CN116146352A - Ultrafiltration ramjet engine spanwise non-uniform fuel pulse injection device and use method - Google Patents
Ultrafiltration ramjet engine spanwise non-uniform fuel pulse injection device and use method Download PDFInfo
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- CN116146352A CN116146352A CN202310439365.3A CN202310439365A CN116146352A CN 116146352 A CN116146352 A CN 116146352A CN 202310439365 A CN202310439365 A CN 202310439365A CN 116146352 A CN116146352 A CN 116146352A
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- Prior art keywords
- fuel
- injection
- main body
- spanwise
- piezoelectric crystal
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- 239000000446 fuel Substances 0.000 title claims abstract description 79
- 238000002347 injection Methods 0.000 title claims abstract description 75
- 239000007924 injection Substances 0.000 title claims abstract description 75
- 238000000034 method Methods 0.000 title claims abstract description 12
- 238000000108 ultra-filtration Methods 0.000 title description 2
- 239000013078 crystal Substances 0.000 claims abstract description 29
- 239000007921 spray Substances 0.000 claims abstract description 24
- 238000004806 packaging method and process Methods 0.000 claims abstract description 15
- 238000002485 combustion reaction Methods 0.000 claims abstract description 13
- 230000007704 transition Effects 0.000 claims abstract description 12
- 238000009434 installation Methods 0.000 claims abstract description 6
- 238000007789 sealing Methods 0.000 claims description 15
- 230000000712 assembly Effects 0.000 claims description 3
- 238000000429 assembly Methods 0.000 claims description 3
- 230000000087 stabilizing effect Effects 0.000 abstract description 4
- 230000000694 effects Effects 0.000 description 4
- 238000001816 cooling Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000002464 physical blending Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
Images
Classifications
-
- 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
-
- 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
- F02C7/24—Heat or noise insulation
-
- 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
The invention discloses a device for injecting fuel in a non-uniform direction in a spanwise direction of a scramjet engine and a use method thereof, which relate to the technical field of fuel injection of a supersonic combustion chamber and have the technical scheme that: the device comprises an injection main body and a packaging panel which are mutually buckled, wherein the injection main body is detachably connected with the packaging panel; a plurality of fuel injection branches are arranged in the injection main body along the expanding direction; the fuel injection branch comprises a fuel branch, a control line channel, a piezoelectric crystal component mounting cavity, a transition pipeline, a transverse pressure equalizing pipeline and a plurality of spray holes; the fuel branch, the control line channel and the transition pipeline are vertically distributed, and the end parts of the fuel branch and the control line channel are communicated with the piezoelectric crystal assembly installation cavity. The device can change the fuel injection mode of the scramjet engine from single mode to multiple mode, and can pertinently adjust the fuel injection quantity of each area and the pulse frequency for assisting the starting ignition according to the starting ignition performance, flame stabilizing performance, combustion efficiency and the like of different areas.
Description
Technical Field
The invention relates to the technical field of fuel injection of a supersonic combustion chamber, in particular to a device for injecting fuel in a non-uniform direction in a spanwise direction of a scramjet engine and a use method thereof.
Background
In the research work of the scramjet engine in the wide speed range, the wave system structure inside the combustion chamber is often changed greatly under the conditions of different engine configurations and different flight Mach numbers, and the change of the wave system structure often leads to uneven distribution of fuel and change of a main combustion area.
For example, under the condition of lower Mach number, the combustion chamber of the open-type concave-cavity scramjet engine is mainly burnt by a shear layer, the fuel consumption of the middle part of the engine along the expanding direction is more, the combustion efficiency of the area close to the side wall is low, and the combustion is weaker, so that the fuel injection on two sides needs to be reduced to increase the equivalent ratio of the fuel in the middle part; under the condition of higher Mach number, a concave cavity is often canceled to serve as a flame stabilizing device, and a support plate is adopted to serve as a flame stabilizer, so that the main flow velocity of the main flow is very high, the side wall effect is very obvious, and the main combustion area is distributed at a position close to the side wall surface, so that the fuel injection quantity in the middle part is required to be reduced, and the equivalence ratio of the fuel on the side wall is increased; in addition, under the condition of high Mach number, the combustion efficiency of fuel is changed from chemical reaction to physical blending effect to be dominant, the pulse injection method can effectively improve the blending effect, improve the starting ignition and flame stabilizing performance of an engine, and meanwhile, pulse injection with higher frequency can achieve the same effect generated by conventional continuous injection, but fuel consumed by the engine can be saved in an injection gap, and the range of an aircraft is indirectly increased.
Disclosure of Invention
The invention aims to provide a device for injecting fuel in a non-uniform direction in a spanwise direction of a scramjet engine and a use method thereof, and the device solves the technical problem in the background art.
The technical aim of the invention is realized by the following technical scheme: the jet body and the packaging panel are detachably connected; a plurality of fuel injection branches are arranged in the injection main body along the expanding direction; the fuel injection branch comprises a fuel branch, a control line channel, a piezoelectric crystal component mounting cavity, a transition pipeline, a transverse pressure equalizing pipeline and a plurality of spray holes; the fuel branch, the control line channel and the transition pipeline are vertically distributed, the end parts of the fuel branch and the control line channel are communicated with the piezoelectric crystal assembly mounting cavity, and the end parts of the fuel branch and the control line channel, which are far away from the piezoelectric crystal assembly mounting cavity, are positioned at the top of the injection main body; the end part of the transition pipeline, which is far away from the piezoelectric crystal assembly mounting cavity, is communicated with the transverse pressure equalizing pipeline; the spray holes are distributed along the expanding direction, the end parts of the spray holes are communicated with the transverse pressure equalizing pipeline, and the end parts of the spray holes, which are far away from the transverse pressure equalizing pipeline, are positioned at the top of the injection main body.
The invention is further provided with: and a piezoelectric crystal control assembly is arranged in the piezoelectric crystal assembly mounting cavity, and a control circuit connected with the piezoelectric crystal control assembly is arranged in the control line channel.
The invention is further provided with: the top of the injection main body is provided with heat-proof grooves with the same quantity as the fuel injection branches, and the heat-proof grooves are communicated with the spray holes.
The invention is further provided with: the injection main body and the packaging panel are provided with threaded holes which are the same in number and correspond to each other, and the injection main body is connected with the packaging panel through bolts.
The invention is further provided with: the sealing device is characterized in that corresponding sealing grooves are formed in the buckling surface of the injection main body and the packaging panel, and sealing strips are arranged in one of the sealing grooves.
The invention is further provided with: the bottom of the injection main body and the sealing panel are matched with each other to form a buckling flange.
The invention also provides a use method of the non-uniform fuel pulse injection device of the scramjet engine, which specifically comprises the following steps:
s1: the device is inserted into a fuel injection assembly installation position of the scramjet engine through a buckling flange, and is fastened and compacted through bolts through the buckling flange;
s2: respectively connecting a plurality of fuel branches into fuel storage tanks with different driving pressures;
s3: after the operation is finished, the opening, closing and movement modes of the piezoelectric crystal control assemblies on the fuel branches are independently controlled by the controller, so that the fuel with different spanwise and non-uniform injection with different pressure, frequency and duty ratio can be obtained at the outlet of the spray hole
In summary, the invention has the following beneficial effects:
1. the device can change the fuel injection mode of the scramjet engine from single mode to diversified mode, and can pertinently adjust the fuel injection quantity of each area and the pulse frequency of auxiliary starting ignition according to the starting ignition performance, flame stabilizing performance, combustion efficiency and the like of different areas;
2. the injection device has good integrity, and the air tightness of internal electronic components is ensured; meanwhile, the heat protection groove is arranged to thermally protect the spray hole, so that the spray hole is not easy to ablate or damage;
3. the device has the advantages of simple and convenient installation method, high structural strength, high safety and convenient replacement of internal elements.
Drawings
FIG. 1 is a schematic diagram of a device for injecting fuel in a spanwise non-uniform fuel pulse in a scramjet engine according to embodiment 1 of the present invention;
FIG. 2 is a cross-sectional view at A-A in FIG. 1;
FIG. 3 is a cross-sectional view at B-B in FIG. 1;
fig. 4 is an enlarged view at a in fig. 1;
fig. 5 is an enlarged view at a in fig. 2;
FIG. 6 is a schematic view showing the structure of the snap-on flange according to embodiment 1 of the present invention;
FIG. 7 is a schematic view showing the structure of an injection body in embodiment 1 of the present invention;
FIG. 8 is a schematic view of the structure of a package panel in embodiment 1 of the present invention;
FIG. 9 is a schematic diagram of a control device for a piezoelectric transistor according to embodiment 1 of the present invention;
fig. 10 is an assembly schematic of the scramjet engine spanwise non-uniform fuel pulse injection apparatus according to embodiment 2 of the present invention mounted on a scramjet engine model.
In the figure: 1. injecting the main body; 2. packaging the panel; 3. a buckling flange; 4. a fuel branch; 5. a control line channel; 6. a piezoelectric crystal assembly mounting cavity; 7. a transition pipeline; 8. a transverse equalizing pipeline; 9. a spray hole; 10. a piezoelectric crystal control assembly; 11. a heat-proof groove; 12. sealing grooves; 13. and (3) a threaded hole.
Description of the embodiments
The invention is described in further detail below with reference to fig. 1-10.
Example 1: the scramjet and engine spanwise non-uniform fuel pulse injection device comprises an injection main body 1 and a packaging panel 2 which are mutually buckled, wherein the buckling surfaces of the injection main body 1 and the packaging panel 2 are provided with corresponding sealing grooves 12, and one sealing groove 12 is internally provided with a sealing strip, so that the piezoelectric crystal control assembly 10 can be conveniently replaced, the tightness is ensured, and the electronic components and control circuits are not ablated; three independent fuel injection branches are arranged in the injection main body 1 along the expanding direction; the positions of the three fuel injection branches are calculated from the side wall and are respectively positioned at 1/6,1/2 and 5/6 of the full width along the spanwise direction; the fuel injection branch comprises a fuel branch 4, a control line channel 5, a piezoelectric crystal component mounting cavity 6, a transition pipeline 7, a transverse pressure equalizing pipeline 8 and five spray holes 9; the fuel branch 4, the control line channel 5 and the transition pipeline 7 are vertically distributed, the end parts of the fuel branch 4 and the control line channel 5 are communicated with the piezoelectric crystal assembly mounting cavity 6, and the end parts of the fuel branch 4 and the control line channel 5, which are far away from the piezoelectric crystal assembly mounting cavity 6, are positioned at the top of the injection main body 1 and are communicated with the outside; the three fuel branches 4 are all connected into a fuel storage tank, and the end part of the transition pipeline 7, which is far away from the piezoelectric crystal assembly mounting cavity 6, is communicated with the middle part of the transverse pressure equalizing pipeline 8; the five spray holes 9 are distributed at equal intervals along the spanwise direction, the end parts of the five spray holes 9 are communicated with the transverse equalizing pipeline 8, the diameter of the spray holes 9 is 0.3mm, the depth is 3mm, and the end parts of the five spray holes 9 far away from the transverse equalizing pipeline 8 are positioned at the top of the injection main body 1 to inject fuel into the combustion chamber of the scramjet engine; the bottoms of the injection main body 1 and the sealing panel are provided with buckling and pressing type flanges 3 in a matched manner;
in this embodiment, a piezoelectric crystal control assembly 10 is placed in the piezoelectric crystal assembly mounting cavity 6, and a control line connected to the piezoelectric crystal control assembly 10 is disposed in the control line channel 5 and connected to an external controller.
In the preferred embodiment, the top of the injection main body 1 is provided with heat-proof grooves 11 with the same number as that of fuel injection branches, the heat-proof grooves 11 are wedge-shaped, the depth is 1mm, and the heat-proof grooves 11 with the width of 2mm are communicated with the spray holes 9; by the arrangement, the spray hole 9 can be effectively prevented from being ablated by high-temperature flame when the pulse gap is not injected with fuel (namely oil-free cooling or air film cooling), and the cross section is wedge-shaped, and the depth and the width are small, so that strong shock waves for changing the flow field structure can not be generated.
In this embodiment, the injection body 1 and the package panel 2 are preferably provided with the same number of corresponding screw holes 13, and the injection body 1 is bolted to the package panel 2.
Example 2: the method for using the scramjet and engine spanwise non-uniform fuel pulse injection device is shown in fig. 10, and specifically comprises the following steps:
s1: the device is inserted into a fuel injection assembly installation position of the scramjet engine through a buckling flange 3, and is fastened and compacted through bolts by the buckling flange 3;
s2: the three fuel branches 4 are respectively connected into fuel storage tanks with different driving pressures;
s3: after the operation is finished, the opening, closing and movement modes of the piezoelectric crystal control assemblies 10 on the three fuel branches 4 are independently controlled by the controller, so that the fuel with different spanwise and non-uniform injection with different pressure, frequency and duty ratio can be obtained at the outlet of the spray hole 9.
The present embodiment is only for explanation of the present invention and is not to be construed as limiting the present invention, and modifications to the present embodiment, which may not creatively contribute to the present invention as required by those skilled in the art after reading the present specification, are all protected by patent laws within the scope of claims of the present invention.
Claims (7)
1. The utility model provides a super-combustion ramjet engine spanwise inhomogeneous fuel pulse injection device which characterized by: the packaging panel comprises an injection main body (1) and a packaging panel (2) which are buckled with each other, wherein the injection main body (1) is detachably connected with the packaging panel (2); a plurality of fuel injection branches are arranged in the injection main body (1) along the expanding direction; the fuel injection branch comprises a fuel branch (4), a control line channel (5), a piezoelectric crystal assembly mounting cavity (6), a transition pipeline (7), a transverse pressure equalizing pipeline (8) and a plurality of spray holes (9); the fuel branch (4), the control line channel (5) and the transition pipeline (7) are vertically distributed, the end parts of the fuel branch (4) and the control line channel (5) are communicated with the piezoelectric crystal assembly mounting cavity (6), and the end parts of the fuel branch (4) and the control line channel (5) which are far away from the piezoelectric crystal assembly mounting cavity (6) are positioned at the top of the injection main body (1); the end part of the transition pipeline (7) far away from the piezoelectric crystal assembly installation cavity (6) is communicated with a transverse pressure equalizing pipeline (8); the spray holes (9) are distributed along the spanwise direction, the end parts of the spray holes (9) are communicated with the transverse pressure equalizing pipeline (8), and the end parts of the spray holes (9) far away from the transverse pressure equalizing pipeline (8) are positioned at the top of the injection main body (1).
2. The scramjet engine spanwise non-uniform fuel pulse injection apparatus of claim 1, wherein: a piezoelectric crystal control assembly (10) is arranged in the piezoelectric crystal assembly mounting cavity (6), and a control circuit connected with the piezoelectric crystal control assembly (10) is arranged in the control wire channel (5).
3. The scramjet engine spanwise non-uniform fuel pulse injection apparatus of claim 1, wherein: the top of the injection main body (1) is provided with heat-proof grooves (11) the number of which is the same as that of fuel injection branches, and the heat-proof grooves (11) are communicated with the spray holes (9).
4. The scramjet engine spanwise non-uniform fuel pulse injection apparatus of claim 1, wherein: the injection main body (1) and the packaging panel (2) are provided with threaded holes (13) which are the same in number and correspond to each other, and the injection main body (1) is connected with the packaging panel (2) through bolts.
5. The scramjet engine spanwise non-uniform fuel pulse injection apparatus of claim 1, wherein: the sealing device is characterized in that corresponding sealing grooves (12) are formed in the buckling surface of the injection main body (1) and the packaging panel (2), and sealing strips are arranged in one sealing groove (12).
6. The scramjet engine spanwise non-uniform fuel pulse injection apparatus of claim 1, wherein: the bottom of the injection main body (1) and the bottom of the sealing panel are matched with each other to form a buckling flange (3).
7. The method for using the scramjet engine spanwise non-uniform fuel pulse injection device according to any one of claims 1-6, wherein the method comprises the following steps: the method specifically comprises the following steps:
s1: the device is inserted into a fuel injection assembly installation position of the scramjet engine through a buckling flange (3), and is fastened and compacted through bolts by the buckling flange (3);
s2: connecting a plurality of fuel branches (4) to fuel storage tanks with different driving pressures respectively;
s3: after the operation is finished, the opening, closing and movement modes of the piezoelectric crystal control assemblies (10) on the fuel branches (4) are independently controlled by the controller, namely, the fuel positions with different spreading directions and non-uniform injection with different pressures, frequencies and duty ratios are obtained at the outlet of the spray hole (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310439365.3A CN116146352B (en) | 2023-04-23 | 2023-04-23 | Ultrafiltration ramjet engine spanwise non-uniform fuel pulse injection device and use method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310439365.3A CN116146352B (en) | 2023-04-23 | 2023-04-23 | Ultrafiltration ramjet engine spanwise non-uniform fuel pulse injection device and use method |
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| CN116146352A true CN116146352A (en) | 2023-05-23 |
| CN116146352B CN116146352B (en) | 2023-08-18 |
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| CN116146352B (en) | 2023-08-18 |
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