CN114607526B - Impact model engine for researching tangential unstable combustion of double-liquid-phase propellant - Google Patents
Impact model engine for researching tangential unstable combustion of double-liquid-phase propellant Download PDFInfo
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- CN114607526B CN114607526B CN202210342727.2A CN202210342727A CN114607526B CN 114607526 B CN114607526 B CN 114607526B CN 202210342727 A CN202210342727 A CN 202210342727A CN 114607526 B CN114607526 B CN 114607526B
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 137
- 239000003380 propellant Substances 0.000 title claims abstract description 35
- 239000007791 liquid phase Substances 0.000 title claims abstract description 14
- 239000000446 fuel Substances 0.000 claims abstract description 44
- 239000007800 oxidant agent Substances 0.000 claims abstract description 40
- 238000002347 injection Methods 0.000 claims abstract description 37
- 239000007924 injection Substances 0.000 claims abstract description 37
- 230000001590 oxidative effect Effects 0.000 claims abstract description 34
- 239000007921 spray Substances 0.000 claims abstract description 33
- 239000007788 liquid Substances 0.000 claims abstract description 23
- 238000007789 sealing Methods 0.000 claims abstract description 11
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 8
- 238000005192 partition Methods 0.000 claims abstract description 5
- 238000005507 spraying Methods 0.000 claims abstract description 4
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 19
- 239000001301 oxygen Substances 0.000 claims description 19
- 229910052760 oxygen Inorganic materials 0.000 claims description 19
- 239000000463 material Substances 0.000 claims description 7
- 230000010355 oscillation Effects 0.000 claims description 7
- 230000008602 contraction Effects 0.000 claims description 6
- 230000009977 dual effect Effects 0.000 claims description 5
- 229910001220 stainless steel Inorganic materials 0.000 claims description 5
- 239000010935 stainless steel Substances 0.000 claims description 5
- 239000002737 fuel gas Substances 0.000 claims description 2
- 239000012071 phase Substances 0.000 claims 2
- 238000009527 percussion Methods 0.000 claims 1
- 238000001228 spectrum Methods 0.000 description 6
- 238000013461 design Methods 0.000 description 5
- 230000007246 mechanism Effects 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 230000004888 barrier function Effects 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 230000010349 pulsation Effects 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- OAKJQQAXSVQMHS-UHFFFAOYSA-N Hydrazine Chemical compound NN OAKJQQAXSVQMHS-UHFFFAOYSA-N 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- WFPZPJSADLPSON-UHFFFAOYSA-N dinitrogen tetraoxide Chemical compound [O-][N+](=O)[N+]([O-])=O WFPZPJSADLPSON-UHFFFAOYSA-N 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 239000010425 asbestos Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009530 blood pressure measurement Methods 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
- 229910052895 riebeckite Inorganic materials 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
Abstract
The invention discloses an impact model engine for researching tangential unstable combustion of a double-liquid-phase propellant, which comprises an oxidant liquid collecting cavity, a propellant partition board, an injection panel, a self-excitation cylinder and a combustion chamber; the top surface of the injection panel is provided with a baffle groove which is in sealing fit with the propellant baffle; a fuel liquid collecting cavity is arranged on the injection panel right below the baffle plate groove; a plurality of fuel spray holes are uniformly distributed on the spraying panel which is positioned right below the fuel liquid collecting cavity along the circumferential direction; oxidant spray holes with the same number as the fuel spray holes are uniformly distributed on the spraying panel positioned in the partition plate groove along the circumferential direction; the self-excitation cylinder is coaxially arranged at the upstream end of the combustion chamber, and a self-excitation circular ring of the combustion chamber is formed between the self-excitation cylinder and the combustion chamber; the fuel spray holes are intersected with the corresponding oxidant spray holes, and the intersection points are positioned in the self-excited circular ring of the combustion chamber. The invention can study the high-frequency tangential unstable combustion characteristics of the double-liquid-phase propellant rocket engine and provide guidance for solving unstable combustion in engineering practice.
Description
Technical Field
The invention relates to a model engine, in particular to an impact model engine for researching tangential unstable combustion of a double-liquid-phase propellant.
Background
The double-component liquid rocket engine has high energy density, high specific impulse and high thrust, can conveniently control flow and thrust, and is widely used for various spacecrafts, such as rocket engines, gas generators, rocket engine game machines, satellite attitude and orbit control engines, missile power systems and the like. The two-component liquid phase propellant is usually liquid oxygen/kerosene and an autoignition propellant, wherein the autoignition propellant is usually hydrazine as fuel and dinitrogen tetroxide as oxidant, and has good storage characteristic in liquid state at normal temperature and normal pressure without ignition and high reliability. However, in the practical development process, the liquid rocket engine often has unstable combustion phenomenon, which has become one of the biggest problems for limiting the development of the high-thrust rocket engine. When unstable combustion occurs, engine vibration is caused, thrust is reduced, and performance is reduced; heavy causes the injection panel to burn through and explode, the thrust chamber fails to work, and serious loss is caused. Unstable combustion can be classified into transverse unstable combustion and longitudinal unstable combustion, wherein transverse unstable combustion can be classified into radial unstable combustion and tangential unstable combustion. When tangential unstable combustion occurs, combustion chamber pressure oscillations are coupled with combustion chamber tangential acoustic frequencies, causing severe pressure and heat release oscillations, and causing significant cyclic thermal loading to the injector face plate and combustion chamber wall surfaces, causing ablation of the combustion chamber or injector face plate, with significant destructive effects. Therefore, the tangential unstable combustion mechanism in the liquid rocket engine is deeply researched, the unstable combustion problem is thoroughly solved, and the method has great engineering practice significance.
In researching the tangentially unstable combustion of the liquid rocket engine, a full-size rocket engine is usually adopted, and although the condition is closest to the actual working condition, the full-size rocket engine has the following defects that the improvement is to be carried out:
1. the full-size model engine has high cost and long period, and needs to consume a great deal of manpower, material resources and financial resources. The combustion chamber can not be windowed, a pressure measurement interface can not be opened, the pressure oscillation characteristic and the flame propagation characteristic in the combustion chamber can not be researched, the obtained data are very limited, the unstable combustion mechanism can not be clarified, and the problem of unstable combustion can not be thoroughly solved.
2. When the tangential unstable combustion is researched, the existing model engine is in a normal pressure working condition, the pressure of a combustion chamber is 1 atmosphere to several atmospheres, the supercritical condition is not reached, and the pressure is greatly different from the supercritical pressure in the actual engine.
3. In some researches, a pulse bomb and a pulse gun are adopted to artificially excite tangential unstable combustion, the excited unstable combustion is greatly different from the self-excited unstable combustion in an actual engine, and no pressure oscillation is generated in the process of increasing to form a limit cycle.
4. The degree of modularization is low, manufacturing and processing are difficult, and the influence of geometrical conditions on unstable combustion characteristics is difficult to study.
Disclosure of Invention
The invention aims at solving the technical problems of the prior art, and provides an impact model engine for researching the tangential unstable combustion of a double-liquid-phase propellant, which can research the high-frequency tangential unstable combustion characteristics of the double-liquid-phase propellant rocket engine, can research the influence of injection working conditions (flow and injection pressure drop) on the tangential unstable combustion, the pressure wave propagation characteristics and the unstable combustion generation mechanism, and provides guidance for solving the unstable combustion in engineering practice. In addition, the invention can analyze the thermo-acoustic coupling characteristic when the high-frequency tangential unstable combustion occurs.
In order to solve the technical problems, the invention adopts the following technical scheme:
an impact model engine for researching tangential unstable combustion of a double-liquid-phase propellant comprises an oxidant liquid collecting cavity, a propellant partition board, an injection panel, a self-excitation cylinder and a combustion chamber.
The oxidant liquid collecting cavity, the injection panel and the combustion chamber are sequentially and coaxially sealed and detachably connected along the axial direction.
An oxygen collecting cavity is arranged in the center of the oxidant liquid collecting cavity.
The top surface of the injection panel is provided with a baffle groove which is in sealing fit with the propellant baffle.
A fuel liquid collecting cavity is arranged on the injection panel right below the baffle plate groove.
A plurality of fuel spray holes are evenly distributed on the spraying panel which is positioned right below the fuel liquid collecting cavity along the circumferential direction.
The injection panel positioned in the baffle plate groove is uniformly provided with oxidant spray holes with the same number as the fuel spray holes along the circumferential direction.
The self-excitation cylinder is coaxially arranged at the upstream end of the combustion chamber, and a self-excitation circular ring of the combustion chamber is formed between the self-excitation cylinder and the combustion chamber.
The fuel spray holes are intersected with the corresponding oxidant spray holes, and the intersection points are positioned in the self-excited circular ring of the combustion chamber.
The center of the bottom of the injection panel positioned in the fuel injection hole is provided with a threaded column mounting groove, the center of the upstream end of the self-excited cylinder is coaxially provided with a central threaded column, and the central threaded column can be in threaded connection with the threaded column mounting groove.
By adjusting the diameter and the length of the self-excited cylinder, the influence of the width and the length of the self-excited circular ring of the combustion chamber on the self-excited tangential unstable combustion can be studied.
At least 2 high-frequency pressure sensor interfaces are distributed on the wall surface of the combustion chamber corresponding to the self-excited circular ring of the combustion chamber along the circumferential direction, and each high-frequency pressure sensor interface is internally provided with a high-frequency pressure sensor.
At least 2 high-frequency pressure sensor interfaces are axially distributed on the wall surface of the combustion chamber, and each high-frequency pressure sensor interface is internally provided with a high-frequency pressure sensor.
The wall surface of the combustion chamber is also provided with a low-frequency pressure sensor interface for installing a low-frequency pressure sensor.
The combustion chamber is made of 321 stainless steel materials and can withstand 5Mpa.
The fuel in the fuel collecting cavity is sprayed out through the fuel spray hole, and is impacted with the oxidant sprayed out through the oxidant spray hole in the self-excited circular ring of the combustion chamber, and is spontaneously combusted in the combustion chamber, and self-excited unstable combustion is established, so that a pressure oscillation limit ring is formed; wherein the frequency of the self-excited unstable combustion can reach 6700Hz.
The diameter of each oxidant spray hole is 1mm, and the diameter of each fuel spray hole is 0.8mm.
The Laval nozzle is arranged at the downstream end of the combustion chamber in a coaxial sealing and detachable mode, and the influence of the Laval nozzle contraction ratio on combustion characteristics can be studied by adjusting the Laval nozzle contraction ratio.
The invention has the following beneficial effects:
(1) The rectangular model engine provided by the invention has the advantages of small size and simple structure, greatly saves labor, material resources and time cost, can acquire a large amount of experimental data, and can deeply study the unstable combustion mechanism.
(2) The invention can realize self-excited tangential unstable combustion, the chamber pressure of the combustion chamber is up to 5MPa, the supercritical condition can be reached, and the self-excited tangential unstable combustion in the actual combustion chamber is more nearly realized. In addition, the impact type design naturally has lower stability margin, and can generate spontaneous high-frequency tangential unstable combustion.
(3) By adopting a high-degree modularized design, the interchangeability among all the components is strong, and the influence of the geometric configuration on high-frequency tangential unstable combustion can be studied by changing the injection panel and the central cylinder, so that the high-frequency tangential unstable combustion can be replaced very quickly and conveniently.
(4) The common 321 stainless steel material is adopted, the processing technology is simpler, and the cost is further saved.
(5) The method can study the influence of the injection working condition (flow and injection pressure drop) on the tangential unstable combustion, the pressure wave propagation characteristic and the unstable combustion generation mechanism, and provides guidance for solving the unstable combustion in engineering practice.
(6) The invention also enables analysis of the thermo-acoustic coupling characteristics when high frequency tangential unstable combustion occurs.
Drawings
Fig. 1 shows an exploded view of an impact model engine of the present invention for studying tangential unstable combustion of a dual liquid phase propellant.
Fig. 2 shows a half-section of fig. 1.
Fig. 3 shows a structural view of an injection panel in the present invention.
Figure 4 shows a cross-sectional view of an injector panel of the present invention with a propellant barrier mounted.
FIG. 5 shows an exploded view of an impact model engine of the present invention without a combustion chamber and Laval nozzle.
FIG. 6 shows a structural view of a combustion chamber in the present invention.
Fig. 7 shows a cross-sectional view of a combustion chamber in accordance with the present invention.
Fig. 8 shows a block diagram of a laval nozzle in accordance with the present invention.
Fig. 9 shows a cross-sectional view of a laval nozzle of the present invention.
The method comprises the following steps:
10. an oxidant plenum; 11. an oxidant supply channel; 12. an oxygen high frequency pressure sensor interface; 13. an oxygen low frequency pressure sensor interface; 14. an oxygen collecting tank; 15. sealing ring grooves;
20. a propellant barrier;
30. injecting a panel; 31. a separator tank; 32. a fuel plenum; 321. a fuel supply passage; 33. a fuel injection hole; 34. oxidant nozzle; 35. a threaded post mounting groove; 36. a seal ring;
40. self-exciting cylinder; 41. a central threaded post;
50. a combustion chamber; 51. a high frequency pressure sensor interface; 52. a low frequency pressure sensor interface;
60. a Laval nozzle; 61. a throat.
Detailed Description
The invention will be described in further detail with reference to the accompanying drawings and specific preferred embodiments.
In the description of the present invention, it should be understood that the terms "left", "right", "upper", "lower", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and "first", "second", etc. do not indicate the importance of the components, and thus are not to be construed as limiting the present invention. The specific dimensions adopted in the present embodiment are only for illustrating the technical solution, and do not limit the protection scope of the present invention.
As shown in fig. 1 and 2, an impact model engine for studying tangential unstable combustion of a dual liquid phase propellant includes an oxidizer plenum 10, a propellant barrier 20, an injection faceplate 30, a self-exciting cylinder 40, a combustion chamber 50, and a laval nozzle 60.
The oxidant liquid collecting cavity, the injection panel, the combustion chamber and the Laval nozzle are coaxially and sequentially sealed and detachably connected in the axial direction, and preferably are in threaded connection. The specific sealing mode is preferably as follows: between the mating surfaces, a seal ring groove 15 and a seal ring 36 are provided which are in sealing engagement with each other as shown in fig. 5. Sealing elements such as asbestos gaskets and the like which are known in the prior art can be additionally arranged between the sealing matching surfaces.
An oxygen collecting cavity is arranged in the center of the oxidant liquid collecting cavity. In this embodiment, an oxygen collecting groove 14 with an opening at the bottom is provided at the center of the bottom surface of the oxidizer liquid collecting cavity, and the oxygen collecting groove is in sealing fit with the top surface of the injection panel to form an oxygen collecting cavity. Of course, other arrangements known in the art may be used.
In addition, an oxidizer supply channel 11 is provided at the top center of the oxidizer collection chamber for supplying the oxidizer in a liquid state to the oxidizer collection chamber.
Further, an oxygen high-frequency pressure sensor interface 12 and an oxygen low-frequency pressure sensor interface 13 are also arranged at the top of the oxidant liquid collecting cavity.
The oxygen high-frequency pressure sensor interface 12 is used for installing an oxygen high-frequency pressure sensor, and the oxygen high-frequency pressure sensor can be used for detecting high-frequency pressure pulsation information in an oxygen collecting cavity, wherein the high-frequency spectrum is 1 kHz-10 kHz, and the high-frequency spectrum is similar to the high-frequency spectrum below.
The oxygen low-frequency pressure sensor interface 13 is used for installing an oxygen low-frequency pressure sensor, and the oxygen low-frequency pressure sensor can be used for detecting low-frequency pressure pulsation information in an oxygen collecting cavity, wherein the low-frequency spectrum is within 1kHz, and the low-frequency spectrum is similar to the low-frequency spectrum below.
As shown in fig. 3-5, the top surface of the injector face plate is provided with a baffle slot 31 in sealing engagement with a propellant baffle, which is preferably sealed and welded within the baffle slot.
The injection panel located directly below the diaphragm groove is provided with a fuel plenum 32 which is connected to an external fuel supply via a fuel supply channel 321 provided in the injection panel.
A plurality of fuel spray holes 33 are uniformly distributed on the injection panel right below the fuel collecting cavity along the circumferential direction, and the diameter of each fuel spray hole is 0.8mm and inclines towards the axis direction of the injection panel.
The injection panel inside the baffle plate groove is uniformly provided with oxidant spray holes 34 with the same number as the fuel spray holes along the circumferential direction, and the diameter of each oxidant spray hole is 1mm and inclines towards the axial direction deviating from the injection panel.
Further, the center of the bottom of the injection panel inside the fuel injection orifice is preferably provided with a threaded post mounting slot 35.
The present invention employs a highly modular design that allows for investigation of the impact of impingement nozzle geometry on combustion characteristics (e.g., impingement angle, diameter of oxidant and fuel orifices, etc.) by altering the injection panel 30.
The combustion chamber is preferably made of 321 stainless steel material, is cylindrical, has a diameter of 60 cm and can withstand 5Mpa. In the invention, the whole model engine is preferably made of 321 stainless steel materials, the processing technology is simpler, and the cost is further saved.
The self-excitation cylinder is coaxially arranged at the upstream end of the combustion chamber, and a central threaded column 41 is preferably coaxially arranged at the center of the upstream end of the self-excitation cylinder and can be in threaded connection with the threaded column mounting groove.
For ease of rectification, the upstream end of the self-exciting cylinder may be designed as a cone.
A combustion chamber self-excitation circular ring is formed between the self-excitation cylinder and the combustion chamber.
The fuel spray holes are intersected with the corresponding oxidant spray holes, and the intersection points are positioned in the self-excited circular ring of the combustion chamber.
According to the invention, the influence of the width and the length of the self-excited circular ring of the combustion chamber on the self-excited tangential unstable combustion can be studied by adjusting the diameter and the length of the self-excited cylinder.
Furthermore, the invention can also be used for researching the rotary knocking, such as increasing the diameter of a self-excited cylinder to form a very narrow combustion chamber self-excited circular ring, so that the invention can be used for researching the rotary knocking characteristics of the two-component propellant and the relation between tangential unstable combustion and rotary knocking.
At least 2 high-frequency pressure sensor interfaces 51 are distributed on the wall surface of the combustion chamber corresponding to the self-excited circular ring of the combustion chamber along the circumferential direction, and each high-frequency pressure sensor interface is internally provided with one high-frequency pressure sensor. The high-frequency pressure sensor distributed along the circumferential direction can detect high-frequency tangential unstable combustion in the combustion chamber.
At least 2 high-frequency pressure sensor interfaces are axially distributed on the wall surface of the combustion chamber, and each high-frequency pressure sensor interface is internally provided with a high-frequency pressure sensor. The high-frequency pressure sensor arranged along the axial direction can detect high-frequency longitudinal unstable combustion in the combustion chamber.
Further, a low frequency pressure sensor interface 52 is provided on the combustion chamber wall for mounting a low frequency pressure sensor. The low frequency pressure sensor herein can be used to detect low frequency pressure pulsation information within the combustion chamber.
In addition, the combustion chamber may be optically diagnosed by optical windowing (not shown).
The Laval nozzle (also called a nozzle) accelerates the hot gases in the combustion chamber to the speed of sound at the throat 61, creating an acoustic cutoff. The invention can study the influence of the Laval nozzle contraction ratio on the combustion characteristic by adjusting the Laval nozzle contraction ratio. Alternatively, the laval nozzle may be modified to be a plug nozzle.
The fuel in the fuel collecting cavity is sprayed out through the fuel spray hole, and is impacted with the oxidant sprayed out through the oxidant spray hole in the self-excited circular ring of the combustion chamber, so that the propellant is atomized, the self-ignition propellant is not required due to the characteristic of the self-ignition propellant, the oxidant spontaneously combusts in the combustion chamber when meeting the fuel, self-excited unstable combustion is quickly established, a pressure oscillation limit ring is formed, and the unstable combustion characteristic is researched; the combusted fuel gas is discharged through the Laval nozzle, and acoustic cut-off is realized at the throat.
Since unstable combustion can be established rapidly in a very short time (< 30 ms), the experimental duration is about 1 s. In order to simplify the structure of the model engine, the combustion chamber and the spray pipe are cooled by adopting a heat sink, but water cooling or regenerative cooling can also be realized by design.
The applicant has completed the design of the model engine at present, and has found that by carrying out numerical simulation verification on the present invention: the invention can realize self-excitation high-frequency tangential unstable combustion with the frequency as high as 6700Hz.
The preferred embodiments of the present invention have been described in detail above, but the present invention is not limited to the specific details of the above embodiments, and various equivalent changes can be made to the technical solution of the present invention within the scope of the technical concept of the present invention, and all the equivalent changes belong to the protection scope of the present invention.
Claims (5)
1. An impact model engine for researching tangential unstable combustion of a biliquid phase propellant, which is characterized in that: comprises an oxidant liquid collecting cavity, a propellant partition board, an injection panel, a self-excitation cylinder and a combustion chamber;
the oxidant liquid collecting cavity, the injection panel and the combustion chamber are sequentially and coaxially sealed and detachably connected along the axial direction;
an oxygen collecting cavity is arranged in the center of the oxidant liquid collecting cavity;
the top surface of the injection panel is provided with a baffle groove which is in sealing fit with the propellant baffle;
a fuel liquid collecting cavity is arranged on the injection panel part right below the baffle plate groove;
a plurality of fuel spray holes are uniformly distributed on the injection panel part positioned right below the fuel liquid collecting cavity along the circumferential direction;
oxidant spray holes with the same number as the fuel spray holes are uniformly distributed on the spraying panel part positioned in the partition plate groove along the circumferential direction;
the self-excitation cylinder is coaxially arranged at the upstream end of the combustion chamber, and a combustion chamber self-excitation circular ring is formed between the self-excitation cylinder and the inner wall surface of the combustion chamber;
the fuel spray holes are intersected with the corresponding oxidant spray holes, and the intersection points are positioned in the self-excitation circular ring of the combustion chamber;
the downstream end of the combustion chamber is coaxially and hermetically detachably provided with a Laval nozzle, and the influence of the Laval nozzle contraction ratio on the combustion characteristics can be studied by adjusting the Laval nozzle contraction ratio;
the combustion chamber is made of 321 stainless steel material and can withstand 5Mpa;
the fuel in the fuel collecting cavity is sprayed out through the fuel spray hole, and is impacted with the oxidant sprayed out through the oxidant spray hole in the self-excited circular ring of the combustion chamber, so that the propellant is atomized, the self-ignition propellant is not required due to the characteristic of the self-ignition propellant, the oxidant spontaneously combusts in the combustion chamber when meeting the fuel, self-excited unstable combustion is quickly established, a pressure oscillation limit ring is formed, and the unstable combustion characteristic is researched; the burnt fuel gas is discharged through the Laval nozzle, and the acoustic cut-off is realized at the throat part; wherein the frequency of self-excited unstable combustion can reach 6700Hz;
a threaded column mounting groove is formed in the center of the bottom of the injection panel positioned in the fuel injection hole, a central threaded column is coaxially arranged in the center of the upstream end of the self-excitation cylinder, and the central threaded column can be in threaded connection with the threaded column mounting groove;
by adjusting the diameter and the length of the self-excited cylinder, the influence of the width and the length of the self-excited circular ring of the combustion chamber on the self-excited tangential unstable combustion can be studied.
2. The impact model engine for studying tangential unstable combustion of a dual liquid phase propellant of claim 1, wherein: at least 2 high-frequency pressure sensor interfaces are distributed on the wall surface of the combustion chamber corresponding to the self-excited circular ring of the combustion chamber along the circumferential direction, and each high-frequency pressure sensor interface is internally provided with a high-frequency pressure sensor.
3. The impact model engine for studying tangential unstable combustion of a dual liquid phase propellant of claim 2, wherein: at least 2 high-frequency pressure sensor interfaces are axially distributed on the wall surface of the combustion chamber, and each high-frequency pressure sensor interface is internally provided with a high-frequency pressure sensor.
4. A percussion model engine for studying tangential unstable combustion of a biliquid phase propellant according to claim 2 or 3, characterized in that: the wall surface of the combustion chamber is also provided with a low-frequency pressure sensor interface for installing a low-frequency pressure sensor.
5. The impact model engine for studying tangential unstable combustion of a dual liquid phase propellant of claim 1, wherein: the diameter of each oxidant spray hole is 1mm, and the diameter of each fuel spray hole is 0.8mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210342727.2A CN114607526B (en) | 2022-03-31 | 2022-03-31 | Impact model engine for researching tangential unstable combustion of double-liquid-phase propellant |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210342727.2A CN114607526B (en) | 2022-03-31 | 2022-03-31 | Impact model engine for researching tangential unstable combustion of double-liquid-phase propellant |
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| Publication Number | Publication Date |
|---|---|
| CN114607526A CN114607526A (en) | 2022-06-10 |
| CN114607526B true CN114607526B (en) | 2024-01-02 |
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| WO2024074993A1 (en) * | 2022-10-05 | 2024-04-11 | D-ORBIT S.p.A. | Thruster for orbital maneuvers, propulsion system for orbital maneuvers and orbital transport vehicle |
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