CN111895450B - Fuel injection device and engine - Google Patents
Fuel injection device and engine Download PDFInfo
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- CN111895450B CN111895450B CN202010680939.2A CN202010680939A CN111895450B CN 111895450 B CN111895450 B CN 111895450B CN 202010680939 A CN202010680939 A CN 202010680939A CN 111895450 B CN111895450 B CN 111895450B
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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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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
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- Combustion & Propulsion (AREA)
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- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
The embodiment of the invention provides a fuel injection device and an engine, and relates to a liquid jet atomization technology, wherein the fuel injection device comprises a combustion chamber, a confluence cavity, an upstream jet orifice and a downstream jet orifice, and the combustion chamber comprises an air suction port and a jet orifice; the combustion chamber is communicated with the confluence cavity through an upstream spray hole and a downstream spray hole respectively; the upstream spray hole is arranged at one side of the downstream spray hole close to the air suction port at a preset distance; the confluence cavity is used for accommodating liquid fuel; the combustion chamber is used for receiving supersonic air flow input from the outside, and the flow direction of the supersonic air flow is from the air suction port to the air injection port; the upstream jet hole and the downstream jet hole are used for jetting the liquid fuel in the confluence cavity into the combustion chamber so as to realize atomization and crushing of supersonic airflow to the liquid fuel in the jetting process.
Description
Technical Field
The invention relates to the technical field of liquid jet atomization, in particular to a fuel injection device and an engine.
Background
The scramjet engine is an ideal power device and key technology for air-breathing hypersonic flight. When the ramjet engine works under the hypersonic speed condition, the flow speed of high-temperature gas in the flow channel also reaches the supersonic speed state, and the staying time of the gas flow in the engine is very short and is only millisecond-order. When liquid fuel is used as working medium, the working state and combustion efficiency of the engine are directly influenced by the atomization, crushing, main flow mixing and other processes of the liquid jet. Moreover, the rotary detonation engine is one of the novel engines with extremely high thermal cycle efficiency at present, and when liquid fuel is adopted as a working medium, the detonation process of the rotary detonation engine extremely depends on the mixing level of the liquid working medium and steam thereof in an engine flow passage. In the prior art, the injection of the liquid fuel is realized in two modes of support plate injection and wall injection.
For the strut injection scheme, although atomization and fragmentation of liquid fuel can be achieved sufficiently, the existence of the strut can greatly increase engine resistance, so that total pressure loss is large, and even a considerable thermal protection problem can be generated at a high speed. For the wall surface injection scheme, due to the fact that the injection depth is not enough, extra gas media are often required to be introduced, and a structure with a complex design is often required to solve the problem of low combustion efficiency.
In view of the above, it is necessary for those skilled in the art to provide a fuel injection device with a strong mixing effect and a simple structure.
Disclosure of Invention
The invention provides a fuel injection device and an engine.
Embodiments of the invention may be implemented as follows:
in a first aspect, an embodiment of the present invention provides a fuel injection device, including a combustion chamber, a manifold chamber, an upstream nozzle hole and a downstream nozzle hole, where the combustion chamber includes an air suction port and an air injection port;
the combustion chamber is communicated with the confluence cavity through the upstream jet hole and the downstream jet hole respectively;
the upstream spray hole is arranged at one side of the downstream spray hole close to the air suction port at a preset distance;
the confluence cavity is used for accommodating liquid fuel;
the combustion chamber is used for receiving supersonic airflow input from the outside, and the flow direction of the supersonic airflow is from the air suction port to the air injection port;
the upstream jet hole and the downstream jet hole are used for jetting the liquid fuel in the confluence cavity into the combustion chamber, so that the supersonic air flow can atomize and break the liquid fuel in the jetting process.
In an optional embodiment, the opening direction of the upstream nozzle hole and the opening direction of the downstream nozzle hole are both perpendicular to the flow direction of the supersonic air flow;
the structures of the upstream jet hole and the downstream jet hole are consistent, and the vertical projections of the upstream jet hole and the downstream jet hole on the contact surface of the upstream jet hole and the downstream jet hole and the combustion chamber are both circular.
In an alternative embodiment, the preset distance is determined according to the following formula:
L＝αMa0.5*q0.5*d
wherein L is the preset distanceAlpha is preset distance parameter, Ma is simulated Mach number of the spray pipe, q is the ratio of the dynamic pressure of the liquid jet of the liquid fuel to the dynamic pressure of the incoming flow gas of the supersonic air flow,
is the dynamic pressure of the liquid jet of the liquid fuel,
dynamic pressure of incoming flow, ρ, of said supersonic gas flowlIs the density of the liquid fuel in the nozzle hole, ulIs the injection velocity, p, of the liquid fuelgIs the density of the supersonic gas flow u∞D is the diameter of the jet orifice, which is the velocity of the supersonic air flow.
In an alternative embodiment, the number of the upstream nozzle holes is plural, and the number of the downstream nozzle holes is plural;
the upstream spray holes form an upstream spray hole group, the downstream spray holes form a downstream spray hole group, and the upstream spray hole group and the downstream spray hole group are arranged in parallel;
the plane defined by the upstream set of injection holes on the interface with the combustion chamber coincides with the plane defined by the downstream set of injection holes on the interface with the combustion chamber.
In an alternative embodiment, the number of the plurality of upstream nozzle holes is the same as the number of the plurality of downstream nozzle holes, and the plurality of upstream nozzle holes and the plurality of downstream nozzle holes correspond to each other one by one.
In an alternative embodiment, the injection direction of the upstream injection hole and the downstream injection hole is perpendicular to the flow direction of the supersonic air flow.
In an alternative embodiment, the fuel injection apparatus further comprises an igniter disposed in the combustion chamber;
the igniter is used for igniting the liquid fuel injected from the upstream injection hole and the downstream injection hole.
In an alternative embodiment, the combustion chamber includes a re-entrant structure for forming an ignition return region for igniting the liquid fuel injected by the upstream and downstream orifices in the ignition return region.
In an alternative embodiment, the air intake comprises an air intake structure connected to the combustion chamber;
the air suction structure is used for converting outside air into the supersonic speed airflow.
In a second aspect, an embodiment of the present invention provides an engine, including an intake duct, a tail pipe, and the fuel injection apparatus according to any one of the preceding embodiments, wherein the intake duct is connected to the intake port and is configured to intake external air into the combustion chamber;
the tail nozzle is connected with the gas nozzle and used for discharging gas in the combustion chamber.
The beneficial effects of the embodiment of the invention include, for example: by adopting the fuel injection equipment and the engine provided by the embodiment of the invention, the fuel injection equipment comprises a combustion chamber, a confluence cavity, an upstream spray hole and a downstream spray hole, wherein the combustion chamber comprises an air suction port and an air jet; the combustion chamber is communicated with the confluence cavity through the upstream jet hole and the downstream jet hole respectively; the upstream spray hole is arranged at one side of the downstream spray hole close to the air suction port at a preset distance; the confluence cavity is used for accommodating liquid fuel; the combustion chamber is used for receiving supersonic airflow input from the outside, and the flow direction of the supersonic airflow is from the air suction port to the air injection port; the upstream jet hole and the downstream jet hole are used for jetting the liquid fuel in the confluence cavity into the combustion chamber so as to realize atomization and crushing of the liquid fuel by the supersonic airflow in the jetting process, and the fuel jetting equipment with a strong mixing effect and a simple structure is realized by skillfully arranging the upstream jet hole and the downstream jet hole.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
FIG. 1 is a schematic diagram of a fuel injection device according to an embodiment of the present disclosure;
FIG. 2 is a schematic diagram illustrating operation of a fuel injection device according to an embodiment of the present disclosure;
FIG. 3 is a schematic structural view of a fuel injection device according to an embodiment of the present disclosure from another perspective;
fig. 4 is a schematic flowchart illustrating steps of a fuel injection device testing method according to an embodiment of the present disclosure.
Icon: 1-fuel injection device; 10-a combustion chamber; 20-a converging cavity; 30-upstream orifice; 40-downstream orifice.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present invention, it should be noted that if the terms "upper", "lower", "inside", "outside", etc. indicate an orientation or a positional relationship based on that shown in the drawings or that the product of the present invention is used as it is, this is only for convenience of description and simplification of the description, and it does not indicate or imply that the device or the element referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus should not be construed as limiting the present invention.
Furthermore, the appearances of the terms "first," "second," and the like, if any, are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.
It should be noted that the features of the embodiments of the present invention may be combined with each other without conflict.
At present, in aerospace equipment related engines such as a scramjet engine and a rotary detonation engine, a liquefied fuel is commonly used for providing power for the engines, when a liquid fuel is used as a working medium, the efficient combustion of the scramjet engine and the smooth working process of the rotary detonation engine are extremely dependent on the mixing level of the liquid working medium and steam thereof in an engine runner, however, a liquid fuel injection scheme in the prior art is implemented by adopting a support plate injection scheme, and although the purpose of improving the mixing level of the liquid fuel is realized, the total pressure loss is very large due to the increase of the resistance of the engine caused by a support plate structure, and a serious thermal protection problem can be generated at a high speed. The wall jetting mode has the problems of insufficient jetting depth, poor space mixing effect and the like, and particularly when the size of the flow channel is large, the liquid jet cannot realize the large mixing effect of a coverage area with the main flow, and the combustion efficiency cannot be improved; when the bubble atomization jet injection is adopted in the structural form, an additional gas medium is required to be introduced, and the structural design is complex. Referring to fig. 1, fig. 1 is a schematic structural diagram of a fuel injection device 1 according to an embodiment of the present disclosure. The fuel injection device 1 comprises a combustion chamber 10, a converging cavity 20, an upstream nozzle hole 30 and a downstream nozzle hole 40, the combustion chamber 10 comprising an intake port and a jet port.
The combustion chamber 10 is connected to the confluence chamber 20 through the upstream nozzle holes 30 and the downstream nozzle holes 40, respectively.
The upstream nozzle hole 30 is disposed at a predetermined distance on a side of the downstream nozzle hole 40 close to the suction port.
The manifold chamber 20 is for containing liquid fuel.
The combustion chamber 10 is used for receiving supersonic air flow input from the outside, and the flow direction of the supersonic air flow is from the air suction port to the air injection port.
Both the upstream nozzle holes 30 and the downstream nozzle holes 40 are used for injecting the liquid fuel in the confluence chamber 20 into the combustion chamber 10 to achieve atomization and fragmentation of the liquid fuel by supersonic air flow during injection.
In the embodiment of the present invention, the combustion chamber 10 may include an air inlet and an air outlet as a space for atomizing and breaking the liquid fuel, wherein the air inlet is used for sucking external air and converting the external air into supersonic air, and the supersonic air can atomize and break the liquid fuel injected from the upstream nozzle 30 and the downstream nozzle 40. The upstream nozzle hole 30 is disposed at a predetermined distance on the side of the downstream nozzle hole 40 close to the suction port, and it can be considered that the upstream nozzle hole 30 is upstream of the supersonic air flow and the downstream nozzle hole 40 is downstream of the supersonic air flow.
On the basis, please refer to fig. 2 and fig. 2 in combination, based on the above arrangement, the liquid fuel injected from the upstream nozzle 30 forms a first bow shock wave C under the influence of the supersonic airflow in the liquid fuel injected from the upstream nozzle 301First bow shock wave C1The liquid fuel is rapidly compressed, the flowing direction of the liquid fuel is rapidly changed from a vertical direction to a main flowing direction (namely the flowing direction of supersonic air flow), secondary atomization and crushing processes are completed under the action of aerodynamic force generated by the supersonic air flow, under the interaction of the supersonic air flow and the liquid fuel sprayed out from the upstream spray holes 30, a low-speed backflow area D is formed at a position close to the converging cavity 20 and right below the spraying position of the upstream spray holes 30, meanwhile, the jet trail area W formed by jet flow is low in speed before insufficient development, the air flow speeds of the low-speed backflow area D and the jet trail area W are subsonic, and the dynamic pressure is lower compared with the supersonic air flow, so that when the downstream spray holes 40 are arranged in the range, the liquid jet flow sprayed out from the downstream spray holes 40 can more easily and directly pass through the low-speed backflow area D and the low-speed backflow area WThe jet flow wake region W reaches the main flow region in a supersonic flow state and generates a second bow shock wave C under the interaction with the main flow2And finishing the secondary atomization and crushing process. With the above arrangement, the nozzle hole areas and the injection pressures of the upstream nozzle hole 30 and the downstream nozzle hole 40 can be kept the same, and the injection depths can be different from each other. Specifically, after the liquid fuel sprayed from the upstream nozzle hole 30 is mixed with the supersonic airflow, the mixture mainly covers the area of the combustion chamber 10 close to the upstream nozzle hole 30, and after the liquid fuel sprayed from the downstream nozzle hole 40 is mixed with the supersonic airflow, the mixture mainly covers the area of the combustion chamber 10 far from the downstream nozzle hole 40, so that different levels and different areas are mixed, the mixing effect is enhanced, and higher combustion efficiency can be realized.
On the basis, please refer to fig. 3 in combination, the opening direction of the upstream nozzle 30 and the opening direction of the downstream nozzle 40 are both perpendicular to the flow direction of the supersonic air flow. The structures of the upstream nozzle holes 30 and the downstream nozzle holes 40 are consistent, and the vertical projections of the upstream nozzle holes 30 and the downstream nozzle holes 40 on the contact surface with the combustion chamber 10 are circular. Based on this, the preset distance may be determined by the following formula:
L＝αMa0.5*q0.5*d
wherein L is a preset distance, alpha is a preset distance parameter, Ma is a simulated Mach number of the spray pipe, q is the ratio of the dynamic pressure of liquid jet of liquid fuel to the dynamic pressure of incoming flow gas of supersonic air flow,
is the dynamic pressure of the liquid jet of the liquid fuel,
dynamic pressure of incoming air, p, for supersonic air flowlIs the density of the liquid fuel in the nozzle hole, ulIs the injection velocity, p, of the liquid fuelgIs the density of supersonic air flow, u∞D is the diameter of the orifice, which is the velocity of the supersonic air flow.
It should be noted that, in the embodiment of the present invention, the preset distance L is taken as an important parameter, the preset distance parameter α used for calculation may be 4 to 5, the simulated mach number Ma of the nozzle may be 1.5 to 3, and the ratio q between the dynamic pressure of the liquid jet of the liquid fuel and the dynamic pressure of the incoming flow gas of the supersonic air flow is usually calculated as 4 to 9, it should be understood that the relevant values of the above parameters may be applicable to the conventional scramjet engine, the rotary detonation engine and other aerospace devices, and in other embodiments of the embodiment provided by the present invention, based on the criterion that the larger the mach number of the incoming flow is, the larger the range of the low-speed area after the jet flow in the direction is, the larger the preset distance L may be obtained, and under a given working condition of the incoming flow (i.e. the relevant parameter of the supersonic air flow), the larger the dynamic pressure ratio is, the deeper the front jet flow penetrates, larger distances can significantly increase the distribution range. Through the arrangement, the problem that other gas media are required to be added or a complex auxiliary structure is required to be designed in the traditional wall surface injection scheme so as to improve the mixing effect is solved, and the mixing effect can be realized without a new structure.
In addition to the above, the number of the upstream nozzle holes 30 is plural, and the number of the downstream nozzle holes 40 is plural.
The plurality of upstream nozzle holes 30 form an upstream nozzle hole group, and the plurality of downstream nozzle holes 40 form a downstream nozzle hole group, which are arranged in parallel.
The plane defined by the upstream set of holes at the interface with the combustion chamber 10 coincides with the plane defined by the downstream set of holes at the interface with the combustion chamber 10.
On this basis, the number of the plurality of upstream nozzle holes 30 is the same as the number of the plurality of downstream nozzle holes 40, and the plurality of upstream nozzle holes 30 and the plurality of downstream nozzle holes 40 correspond one to one.
The number of the plurality of upstream nozzle holes 30 is the same as that of the plurality of downstream nozzle holes 40, the arrangement positions may be in one-to-one correspondence, the nozzle holes are uniformly distributed, and the plurality of upstream nozzle holes 30 and the plurality of downstream nozzle holes 40 are all arranged on the same horizontal plane.
On the basis of the above, the injection directions of the upstream injection hole 30 and the downstream injection hole 40 are perpendicular to the flow direction of the supersonic air flow.
In the embodiment of the invention, the injection direction is consistent with the opening direction of the spray hole so as to ensure the completeness of atomization and crushing after the liquid fuel is injected.
In addition to the aforementioned structure, the fuel injection device 1 further comprises an igniter, which is arranged in the combustion chamber 10. The igniter is used to ignite the liquid fuel injected through the upstream and downstream orifices 30, 40. After the liquid fuel is atomized and pulverized again by the structure, and is ignited after being fully mixed, the supersonic airflow is ejected from the air nozzle, and it is understood that the igniter is ready before the liquid fuel is injected.
In other embodiments of the disclosed embodiments, the combustion chamber 10 includes a re-entrant structure that is configured to form an ignition return zone such that liquid fuel injected through the upstream nozzle holes 30 and the downstream nozzle holes 40 is ignited in the ignition return zone. In order to meet some special requirements, an igniter can be omitted, a concave cavity structure can be arranged in the combustion chamber 10, a backflow area can be generated locally, the flow speed of the backflow area is low, the static temperature is high, and the static temperature exceeds the ignition point of fuel, so that ignition is realized.
On the basis of the foregoing, the intake port includes an intake structure, which is connected to the combustion chamber 10. The air suction structure is used for converting outside air into supersonic speed air flow, and the air suction structure can be specifically an incoming flow air generating device.
In order to be able to describe more clearly the feasibility of the previously provided fuel injection device 1, an example of a test carried out with the previously described fuel injection device 1 is described below.
In the embodiment provided by the invention, the cross section of the internal flow passage of the combustion chamber 10 of the ramjet engine is generally a rectangular structure, while the cross section of the internal flow passage of the rotary detonation engine is generally of a circular ring design and is also approximately a rectangular structure if the internal flow passage is partially cut, so that the corresponding structure of the embodiment of the invention is a rectangular structure or a partially rectangular structure. A particular combustor 10 size may be 35mm in height and 58mm in width with a rectangular configuration of about 200mm in length.
In the embodiment of the present invention, the number of the upstream nozzle holes 30 may be four, the number of the downstream nozzle holes 40 is also four, the distance between each upstream nozzle hole 30 may be 10mm, the distance between each downstream nozzle hole 40 may also be 10mm, and the one-to-one correspondence is made, the preset distance L between the upstream nozzle hole 30 and the downstream nozzle hole 40 may be 7mm, the diameter d of each nozzle hole may be 0.5mm, and the flow coefficient of the supersonic air flow during the test may be between 0.68 and 0.74.
In particular, with reference to fig. 4, the following experimental procedure is provided, the fuel injection device 1 being connected to a measurement system.
Step S201, checking test parameters and preparing a measurement system.
In step S202, the inflow air generating device (i.e., the air intake structure) upstream of the combustion chamber 10 starts operating, and the measurement system starts operating.
In step S203, liquid fuel injection is started and the measurement system continues to operate.
In step S204, liquid fuel injection is stopped.
And step S205, stopping the operation of the incoming flow air generating device, and stopping the operation of the measuring system.
Through the test steps, test parameters are measured as follows: the mach number of the incoming flow Ma2.0, the total pressure of the incoming flow 0.95MPa, the dynamic pressure of the incoming flow 0.33MPa, the total temperature of the incoming flow 950K, the injection pressure 2.88MPa, the flow coefficient of an injection hole 0.74, the injection dynamic pressure 1.58MPa, and the corresponding injection/incoming flow dynamic pressure ratio q is 4.79. Based on the formula L ═ α Ma for calculating the preset distance0.5*q0.5D, L ═ (4 to 5)1.55 ═ 6.2 to 7.75 mm. The preset distance L provided above may be set to coincide with 7 mm.
The embodiment of the invention provides an engine which can be a ramjet engine and comprises an air inlet channel, a tail nozzle and the fuel injection device 1, wherein the air inlet channel is connected with an air suction port and is used for sucking external air into a combustion chamber 10. The tail pipe is connected with a gas nozzle for discharging gas in the combustion chamber 10.
In summary, embodiments of the present invention provide a fuel injection device and an engine, where the fuel injection device includes a combustion chamber, a manifold chamber, an upstream nozzle hole and a downstream nozzle hole, and the combustion chamber includes an air intake and an air injection; the combustion chamber is communicated with the confluence cavity through the upstream jet hole and the downstream jet hole respectively; the upstream spray hole is arranged at one side of the downstream spray hole close to the air suction port at a preset distance; the confluence cavity is used for accommodating liquid fuel; the combustion chamber is used for receiving supersonic airflow input from the outside, and the flow direction of the supersonic airflow is from the air suction port to the air injection port; the upstream jet hole and the downstream jet hole are used for jetting the liquid fuel in the confluence cavity into the combustion chamber so as to realize atomization and crushing of the liquid fuel by the supersonic airflow in the jetting process, and the fuel jetting equipment with a strong mixing effect and a simple structure is realized by skillfully arranging the upstream jet hole and the downstream jet hole.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (8)
1. A fuel injection device, comprising a combustion chamber, a manifold, an upstream orifice and a downstream orifice, the combustion chamber comprising an air intake and an air jet;
the combustion chamber is communicated with the confluence cavity through the upstream jet hole and the downstream jet hole respectively;
the upstream spray hole is arranged at one side of the downstream spray hole close to the air suction port at a preset distance;
the confluence cavity is used for accommodating liquid fuel;
the combustion chamber is used for receiving supersonic airflow input from the outside, and the flow direction of the supersonic airflow is from the air suction port to the air injection port;
the upstream jet hole and the downstream jet hole are used for injecting the liquid fuel in the confluence cavity into the combustion chamber so as to realize atomization and fragmentation of the liquid fuel by the supersonic airflow during injection;
the opening direction of the upstream spray hole and the opening direction of the downstream spray hole are both vertical to the flow direction of the supersonic velocity airflow;
the structures of the upstream jet hole and the downstream jet hole are consistent, and the vertical projections of the upstream jet hole and the downstream jet hole on the contact surface of the upstream jet hole and the downstream jet hole and the combustion chamber are both circular;
the preset distance is determined according to the following formula:
L＝αMa0.5*q0.5*d
wherein L is the preset distance, alpha is a preset distance parameter, Ma is a simulated Mach number of the spray pipe, q is a ratio of a dynamic pressure of a liquid jet of the liquid fuel to a dynamic pressure of incoming flow gas of the supersonic air flow,
is the dynamic pressure of the liquid jet of the liquid fuel,
dynamic pressure of incoming flow, ρ, of said supersonic gas flowlIs the density of the liquid fuel in the nozzle hole, ulIs the injection velocity, p, of the liquid fuelgIs the density of the supersonic gas flow u∞D is the diameter of the jet orifice, which is the velocity of the supersonic air flow.
2. The fuel injection device according to claim 1, wherein the upstream nozzle hole is plural in number, and the downstream nozzle hole is plural in number;
the upstream spray holes form an upstream spray hole group, the downstream spray holes form a downstream spray hole group, and the upstream spray hole group and the downstream spray hole group are arranged in parallel;
the plane defined by the upstream set of injection holes on the interface with the combustion chamber coincides with the plane defined by the downstream set of injection holes on the interface with the combustion chamber.
3. The fuel injection device according to claim 2, wherein the number of the plurality of upstream nozzle holes is the same as the number of the plurality of downstream nozzle holes, and the plurality of upstream nozzle holes and the plurality of downstream nozzle holes correspond one-to-one.
4. The fuel injection device of claim 1, wherein injection directions of said upstream nozzle orifice and said downstream nozzle orifice are perpendicular to a flow direction of said supersonic gas flow.
5. The fuel injection apparatus of claim 1, further comprising an igniter disposed in said combustion chamber;
the igniter is used for igniting the liquid fuel injected from the upstream injection hole and the downstream injection hole.
6. The fuel injection device of claim 1, wherein said combustion chamber includes a re-entrant structure for forming a firing recirculation zone in which said liquid fuel injected by said upstream and downstream orifices ignites.
7. A fuel injection device as in claim 1 wherein said intake port comprises an intake structure connected to said combustion chamber;
the air suction structure is used for converting outside air into the supersonic speed airflow.
8. An engine comprising an intake port, a jet nozzle and a fuel injection device according to any one of claims 1 to 7;
the air inlet channel is connected with the air suction port and used for sucking external air into the combustion chamber;
the tail nozzle is connected with the gas nozzle and used for discharging gas in the combustion chamber.
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| CN102966974A (en) * | 2012-12-18 | 2013-03-13 | 中国人民解放军国防科学技术大学 | Supersonic combustor wall surface concave cavity structure and engine combustor comprising same |
| CN103499107A (en) * | 2013-09-11 | 2014-01-08 | 中国科学院力学研究所 | Supersonic combustor with heated kerosene as fuel |
| 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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