CN115682032B - A new type of multi-ring fuel support plate injector - Google Patents
A new type of multi-ring fuel support plate injector Download PDFInfo
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- CN115682032B CN115682032B CN202211369042.3A CN202211369042A CN115682032B CN 115682032 B CN115682032 B CN 115682032B CN 202211369042 A CN202211369042 A CN 202211369042A CN 115682032 B CN115682032 B CN 115682032B
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- fuel
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- support plates
- annular support
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- 239000000446 fuel Substances 0.000 title claims abstract description 123
- 238000002347 injection Methods 0.000 claims abstract description 70
- 239000007924 injection Substances 0.000 claims abstract description 70
- 238000002485 combustion reaction Methods 0.000 claims abstract description 29
- 238000003491 array Methods 0.000 claims abstract description 10
- 230000003247 decreasing effect Effects 0.000 claims description 4
- 230000007423 decrease Effects 0.000 abstract description 3
- 238000002156 mixing Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002146 bilateral effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000007935 neutral effect Effects 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 230000007306 turnover Effects 0.000 description 1
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- Fuel-Injection Apparatus (AREA)
Abstract
The invention discloses a novel multi-ring type fuel support plate injector which comprises at least two layers of annular support plates, four equal-straight support plates and fuel supply channels, wherein the annular support plates are coaxially arranged in a combustion chamber of a rocket engine at intervals, the diameters of the annular support plates decrease along the air inflow direction of the combustion chamber, each annular support plate is provided with an annular fuel channel which is arranged in the annular support plate, two rings of injection hole arrays are arranged on two sides of the annular support plate in an inner and outer encircling mode, each ring of injection hole array comprises a plurality of injection holes which are uniformly arranged, each injection hole is communicated with the annular fuel channel, the four equal-straight support plates are communicated between the annular support plates, and the fuel supply channels are arranged in the inner parts of the equal-straight support plates along the trend of the equal-straight support plates. The problem that the injection area of the existing injector is uneven and the injection density is uncontrollable is solved.
Description
Technical Field
The invention belongs to the technical field of scramjet engines or combined power engines, and particularly relates to a novel multi-ring type fuel support plate injector.
Background
The rocket-based ramjet combined cycle (RBCC) engine is a novel combined power form combining a rocket engine and a ramjet engine, so that the RBCC engine combines the advantages of high thrust-weight ratio of the rocket engine and high specific impulse of the ramjet engine, and further the aircraft can realize wide-range speed adjustment from zero-speed take-off to high Mach number flight, thereby greatly improving task adaptability and having great development potential in future near-ground air-day transportation.
The RBCC engine is divided into four modes, namely an ejection mode, a sub-combustion punching mode, a scramjet mode and a rocket mode. In the first three modes, the ramjet engine needs to be ignited, and the combustion is organized in the engine combustion chamber, and fuel required for combustion is injected by a plurality of support plates installed in the ramjet engine. Most of the currently applied fuel support plates are equal-straight support plates, the support plates are uniformly arranged in front of an engine combustion chamber, and the side wall or the back wall of the support plates is perforated and connected with an oil supply pipeline to realize fuel injection. However, when the support plate is used for injecting in a large-size circular combustion chamber, due to limited fuel injection penetration depth, the phenomenon that fuel injection areas overlap in the center area of a flow field and a fuel injection area is neutral in the near-wall area of the flow field can be generated, so that the mixing efficiency and combustion stability of fuel and incoming flow are affected. In addition, pilot fuel injection is also an important topic of research in combined power ramjet engines.
In RBCC engines, the design of the fulcrum plate has an important impact on the blending of fuel with incoming flow, and subsequent combustion. As RBCC evolves, the engine size will necessarily expand, and in large scale circular flow field structures, the impact of the arrangement of fuel struts on injection uniformity and blending efficiency will expand further.
Disclosure of Invention
The invention aims to provide a novel multi-ring type fuel support plate injector, which aims to solve the problems of non-uniform injection area and uncontrollable injection density of the existing injector.
The invention adopts the following technical scheme that the novel multi-ring type fuel support plate injector is positioned in a combustion chamber and comprises:
At least two layers of annular support plates are coaxially arranged in a combustion chamber of the rocket engine at intervals, and the diameters of the annular support plates are gradually decreased along the air inflow direction of the combustion chamber;
Each annular support plate is provided with:
An annular fuel passage arranged inside the annular support plate;
Two circles of injection hole arrays, wherein the inner ring and the outer ring are arranged on two sides of the annular support plate in a surrounding way, each circle of injection hole array comprises a plurality of injection holes which are uniformly arranged, and each injection hole is communicated with the annular fuel channel;
The four equal straight support plates are communicated and arranged between the annular support plates, and a fuel supply channel is arranged in each equal straight support plate along the trend of the equal straight support plate;
wherein each fuel supply passage communicates with the annular fuel passage intersecting therewith, each fuel supply passage for delivering fuel to each annular fuel passage and injecting fuel outwardly through each injection hole.
Furthermore, the annular fuel channels in each annular support plate are symmetrically divided into four sections of arc-shaped fuel channels which are not communicated with each other, the center of symmetry is the center of the circle of the annular support plate, and the arc-shaped fuel channels on the same side of each layer of annular support plate are communicated through an equal straight support plate to form an independent fuel channel unit.
Further, in one fuel channel unit, the density of the injection holes in each turn of the injection hole array on the arcuate fuel channels of each layer gradually decreases in the direction outward from the center of the flow field.
Further, each equal straight support plate is fixed on the inner wall surface of the combustion chamber, and one end of each equal straight support plate is provided with a fuel supply inlet in a communicating mode.
The invention has the beneficial effects that through double-side injection and arc-shaped fuel channel arrangement on the annular support plate, the full coverage of the injection of the cross section area of the convection field and the control of the fuel injection density gradient from the central area of the flow field to the near-wall area of the flow field can be realized by independently changing the fuel flow rate in the fuel supply channels of all the equal-straight support plates, independently changing the flow area of all the arc-shaped fuel channels, or independently changing the injection hole density in all the circles of injection hole arrays.
Drawings
FIG. 1 is a schematic perspective view of a novel multi-ring fuel strip injector of the present invention;
FIG. 2 is a schematic axial cross-sectional view of a novel multi-ring fuel strip injector of the present invention along an equal straight strip;
FIG. 3 is a schematic view of the structure of a novel multi-ring fuel strip injector of the present invention projected in the direction of air flow;
FIG. 4 is an enlarged schematic view at C in FIG. 3;
FIG. 5 is a schematic partial cross-sectional view of a junction of a circular support plate and an equal straight support plate of a novel multi-ring fuel support plate injector of the present invention.
The fuel injection device comprises an annular support plate 1, an equal-straight support plate 2, an injection hole 3, a fuel supply inlet 4, a fuel supply channel 5, an annular fuel channel 6, a combustion chamber inner wall surface 7 and a connecting flange plate 8.
Detailed Description
The invention will be described in detail below with reference to the drawings and the detailed description.
The invention provides a novel multi-ring type fuel support plate injector, which is shown in figure 1 and is positioned in a combustion chamber of a rocket engine, wherein connecting flanges 8 are arranged at two ends of the combustion chamber and comprise at least two layers of annular support plates 1 and four equal-straight support plates 2.
The annular support plates 1 of each layer are coaxially arranged at intervals, and the diameters of the annular support plates 1 of each layer are gradually decreased along the air inflow direction of the combustion chamber. As shown in fig. 3, each annular support plate 1 has the same structure, and as shown in fig. 5, the annular support plate 1 includes an annular fuel passage 6 and two ring injection hole arrays. The annular support plate 1 of each layer is internally provided with an annular fuel channel 6, the wall surface of the inner ring and the wall surface of the outer ring of the annular support plate 1 of each layer are respectively provided with a circle of injection hole arrays, each circle of injection hole arrays comprises a plurality of injection holes 3 which are uniformly arranged, and each injection hole 3 is communicated with the annular fuel channel 6.
The annular support plates 1 used in the invention all adopt bilateral fuel injection, so that fuel can be tiled into an incoming flow field along multiple angles, the fuel injection coincidence of the central area of the flow field is reduced, the fuel injection coverage of the edge area of the flow field is increased, the circumferential uniformity of fuel injection in the flow field is improved, and the total injection coverage incoming flow sectional area is increased. For engines of different sizes, an increase in fuel injection coverage area and fuel injection uniformity can be ensured simultaneously by increasing or decreasing the number of annular fuel injection support plates 1.
The plurality of annular support plates 1 are arranged among the equal straight support plates, so that the injection uniformity is improved, meanwhile, the projection area of the equal straight support plates in the incoming flow is reduced, the blocking ratio of the support plates to the incoming flow field is reduced, the total surface area of the support plates in the flow field is reduced, and the structural heat protection burden is reduced. In addition, the total mass of the support plate structure is reduced, and the dry weight of the engine is reduced.
As shown in fig. 1 and 2, four equal-straight support plates 2 are respectively connected and arranged between the annular support plates 1, a fuel supply channel 5 is arranged in the equal-straight support plates 2 along the trend of the equal-straight support plates 2, and the equal-straight support plates 2 are uniformly and alternately arranged. Wherein each fuel supply channel 5 is communicated with the annular fuel channels 6 intersected with the fuel supply channel, each fuel supply channel 5 is used for conveying fuel to each annular fuel channel 6 and injecting the fuel outwards through each injection hole 3, and the fuel moves along the flow direction of a flow field airflow after being injected.
In some embodiments, as shown in fig. 3, the annular fuel channels 6 in each annular support plate 1 are symmetrically divided into four sections of arc-shaped fuel channels which are not communicated with each other, and the center of symmetry is the center of the circle of the annular support plate 1. The fuel flow in the four-segment arc-shaped fuel channels can be independently controlled. The arc-shaped fuel channels on the same side of each layer of annular support plate 1 are communicated through an equal straight support plate 2, and an independent fuel channel unit is formed.
As shown in fig. 3, one fuel passage unit includes one straight stay 2, and a plurality of arc-shaped fuel passages communicating with the straight stay 2. Each annular support plate 1 is divided into four sections of independent arc-shaped fuel channels, so that each part of injection area is separated, each section of the injection area is controllable and adjustable, and meanwhile, the flow between fuel inlets of two adjacent sections of arc-shaped fuel channels is prevented from being influenced mutually. For example, four separate arcuate fuel passages are located at the upper left, lower left, upper right, and lower right positions of the annular support plate 1, respectively. While the arc-shaped fuel passages located in the same fuel passage unit are all located on the same side of the annular support plate 1, for example, arc-shaped fuel passages located in the upper left positions of the respective annular support plates 1 are all communicated through an equal straight support plate 2 and form a fuel passage unit.
In some embodiments, the density of the injection holes in the array of injection holes in each turn over the arcuate fuel channels of each layer in one fuel channel unit decreases progressively in a direction outward from the center of the flow field. As shown in fig. 3, taking the annular support plate 1 as an example of two layers, the densities of the injection holes in the injection hole arrays provided on the inner ring wall surface and the outer ring wall surface of the annular support plate 1 with a smaller diameter are ρ1 and ρ2, respectively, and the densities of the injection holes in the injection hole arrays provided on the inner ring wall surface and the outer ring wall surface of the annular support plate 1 with a larger diameter are ρ3 and ρ4, respectively, then ρ1> ρ2> ρ3> ρ4 are performed in the direction from the center of the flow field. The density of the injection holes near the inner ring of the annular support plate 1 is higher than that near the outer ring of the annular support plate 1, so that the central area can be formed to inject more fuel, the injection quantity near the inner wall surface 7 of the combustion chamber is less, the combustion reaction can be relatively concentrated in the central area of the flow field, the combustion near the inner wall surface 7 of the combustion chamber is reduced, and the heat protection pressure is reduced.
Meanwhile, in the four fuel channel units, the injection hole densities of the arc-shaped fuel channels can be different, so that the free adjustment of the injection density is convenient to realize.
In some embodiments, each of the straight support plates 2 is fixed to the inner wall surface 7 of the combustion chamber, and one end of each of the straight support plates 2 is provided with a fuel supply inlet 4 in a communicating manner. The fuel supply inlet 4 is located at the outer wall of the combustion chamber.
As shown in fig. 5, the cross section of the joint of the annular fuel injection support plate 1 and the equal-straight fuel supply support plate 2 is in a shape of a wedge and a rectangle which are integrally connected, the sharp angle of the wedge is a round, the round radius is 1mm, and the backward inclined angle of the oil supply support plate along the flow field direction is 30 degrees, so that the resistance of air flow in the flow field is reduced, and the heat load of the front edge of the support plate is reduced.
The invention relates to a using method of a novel multi-ring type fuel support plate injector, which comprises the steps of leading fuel into fuel supply channels 5 in each equal-straight support plate 2 through each fuel supply inlet 4, respectively flowing into each section of annular fuel channel 6 of each annular support plate 1, finally spraying out from injection holes 3 of each ring of injection hole array, and burning in a combustion chamber.
According to the invention, through double-side injection and arc-shaped fuel channel arrangement on the annular support plates, the full coverage of the injection of the cross section area of the convection field and the control of the gradient of the injection density of the fuel from the central area of the flow field to the near-wall area of the flow field can be realized by independently changing the fuel flow rate in the fuel supply channels of the equal-straight support plates, independently changing the flow area of each arc-shaped fuel channel, or independently changing the injection hole density in each circle of injection hole array.
Claims (2)
1. A novel multi-ring fuel manifold injector, located in a combustion chamber, comprising:
At least two layers of annular support plates (1) are coaxially arranged in a combustion chamber of the rocket engine at intervals, and the diameter of each annular support plate (1) is gradually decreased along the air inflow direction of the combustion chamber;
each annular support plate (1) is provided with:
an annular fuel passage (6) arranged inside the annular support plate (1);
two circles of injection hole arrays, wherein the inner ring and the outer ring are arranged on two sides of the annular support plate (1), each circle of injection hole array comprises a plurality of injection holes (3) which are uniformly arranged, and each injection hole (3) is communicated with the annular fuel channel (6);
the four equal straight support plates (2), each equal straight support plate (2) is communicated and arranged between the annular support plates (1), and a fuel supply channel (5) is arranged in the equal straight support plates (2) along the trend of the equal straight support plates;
wherein each of the fuel supply passages (5) communicates with the annular fuel passage (6) intersecting therewith, each of the fuel supply passages (5) for delivering fuel to each of the annular fuel passages (6) and injecting fuel outwardly through each of the injection holes (3);
The annular fuel channels (6) in each annular support plate (1) are symmetrically divided into four sections of arc-shaped fuel channels which are not communicated with each other, the symmetrical center is the center of the circle of the annular support plate (1), the arc-shaped fuel channels on the same side of each layer of annular support plate (1) are communicated through an equal straight support plate (2) to form an independent fuel channel unit, and the density of injection holes in each circle of injection hole arrays on each layer of arc-shaped fuel channels in one fuel channel unit is gradually reduced along the direction from the center of a flow field to the outside.
2. A novel multi-ring fuel manifold injector as claimed in claim 1, wherein each of said straight brackets (2) is fixed to the inner wall surface (7) of the combustion chamber, and one end of each of said straight brackets (2) is provided with a fuel supply inlet (4) in communication.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211369042.3A CN115682032B (en) | 2022-11-03 | 2022-11-03 | A new type of multi-ring fuel support plate injector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211369042.3A CN115682032B (en) | 2022-11-03 | 2022-11-03 | A new type of multi-ring fuel support plate injector |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115682032A CN115682032A (en) | 2023-02-03 |
| CN115682032B true CN115682032B (en) | 2025-02-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211369042.3A Active CN115682032B (en) | 2022-11-03 | 2022-11-03 | A new type of multi-ring fuel support plate injector |
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| Country | Link |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102116579A (en) * | 2009-12-30 | 2011-07-06 | 中冶长天国际工程有限责任公司 | Burning pipeline system for rotary hearth furnace |
| CN110793062A (en) * | 2019-10-30 | 2020-02-14 | 北京空天技术研究所 | Scramjet engine and runner structure adopting central combustion |
| CN111023152A (en) * | 2019-12-18 | 2020-04-17 | 西安航天动力研究所 | Rectifying injection integrated device and ramjet using the same |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7854121B2 (en) * | 2005-12-12 | 2010-12-21 | General Electric Company | Independent pilot fuel control in secondary fuel nozzle |
| CN108131684B (en) * | 2017-12-14 | 2019-11-22 | 西北工业大学 | An annular fuel supply integrated afterburner |
| FR3099547B1 (en) * | 2019-07-29 | 2021-10-08 | Safran Aircraft Engines | FUEL INJECTOR NOSE FOR TURBOMACHINE INCLUDING A ROTATION CHAMBER INTERNALLY DELIMITED BY A PIONEER |
| CN114440258A (en) * | 2022-01-11 | 2022-05-06 | 中国人民解放军国防科技大学 | Coaxial injection device of supersonic combustion chamber |
-
2022
- 2022-11-03 CN CN202211369042.3A patent/CN115682032B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102116579A (en) * | 2009-12-30 | 2011-07-06 | 中冶长天国际工程有限责任公司 | Burning pipeline system for rotary hearth furnace |
| CN110793062A (en) * | 2019-10-30 | 2020-02-14 | 北京空天技术研究所 | Scramjet engine and runner structure adopting central combustion |
| CN111023152A (en) * | 2019-12-18 | 2020-04-17 | 西安航天动力研究所 | Rectifying injection integrated device and ramjet using the same |
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| Publication number | Publication date |
|---|---|
| CN115682032A (en) | 2023-02-03 |
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