CN114607526A - Impact type model engine for researching tangential unstable combustion of double-liquid-phase propellant - Google Patents
Impact type model engine for researching tangential unstable combustion of double-liquid-phase propellant Download PDFInfo
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- CN114607526A CN114607526A CN202210342727.2A CN202210342727A CN114607526A CN 114607526 A CN114607526 A CN 114607526A CN 202210342727 A CN202210342727 A CN 202210342727A CN 114607526 A CN114607526 A CN 114607526A
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 142
- 239000003380 propellant Substances 0.000 title claims abstract description 36
- 239000007791 liquid phase Substances 0.000 title claims abstract description 19
- 239000000446 fuel Substances 0.000 claims abstract description 44
- 239000007800 oxidant agent Substances 0.000 claims abstract description 40
- 230000001590 oxidative effect Effects 0.000 claims abstract description 39
- 238000002347 injection Methods 0.000 claims abstract description 34
- 239000007924 injection Substances 0.000 claims abstract description 34
- 239000007788 liquid Substances 0.000 claims abstract description 28
- 239000007921 spray Substances 0.000 claims abstract description 23
- 238000007789 sealing Methods 0.000 claims abstract description 10
- 238000005192 partition Methods 0.000 claims abstract description 8
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 8
- 238000011160 research Methods 0.000 claims abstract description 3
- 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
- 229910001220 stainless steel Inorganic materials 0.000 claims description 5
- 239000010935 stainless steel Substances 0.000 claims description 5
- 239000012071 phase Substances 0.000 claims 1
- 238000013461 design Methods 0.000 description 5
- 230000007246 mechanism Effects 0.000 description 5
- 238000001228 spectrum Methods 0.000 description 5
- 238000005474 detonation Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 230000010349 pulsation Effects 0.000 description 3
- 125000006850 spacer group Chemical group 0.000 description 3
- 230000002269 spontaneous effect Effects 0.000 description 3
- 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
- 238000004880 explosion Methods 0.000 description 2
- 230000013011 mating Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 1
- 239000010425 asbestos Substances 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009530 blood pressure measurement Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 150000002429 hydrazines Chemical class 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 230000000737 periodic 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
- 239000000243 solution Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Fuel-Injection Apparatus (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
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 plate, an injection panel, a self-excitation cylinder and a combustion chamber, wherein the oxidant liquid collecting cavity is provided with a plurality of nozzles; the top surface of the injection panel is provided with a clapboard groove which is in sealing fit with the propellant clapboard; a fuel liquid collecting cavity is formed in the injection panel positioned right below the clapboard groove; a plurality of fuel spray holes are uniformly distributed on the injection panel which is positioned right below the fuel liquid collecting cavity along the circumferential direction; oxidant jet holes with the number equal to that of the fuel jet holes are uniformly distributed on the jet panel 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 ring is formed between the self-excitation cylinder and the combustion chamber; the fuel injection holes and the corresponding oxidant injection holes are arranged in an intersecting mode, and the intersection points are located in the combustion chamber self-excitation circular ring. The invention can research the high-frequency tangential unstable combustion characteristic of the double-liquid-phase propellant rocket engine and provide guidance for solving the unstable combustion in engineering practice.
Description
Technical Field
The invention relates to a model engine, in particular to an impact type 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, and can be widely used for various spacecrafts, such as rocket engines, gas generators, rocket engine touring machines, satellite attitude and orbit control engines, missile power systems and the like, and the flow and the thrust can be conveniently controlled. The bipropellant liquid propellant is usually liquid oxygen/kerosene and spontaneous combustion propellant, wherein the spontaneous combustion propellant usually uses hydrazines as fuel, uses dinitrogen tetroxide as oxidant, is in a liquid state at normal temperature and normal pressure, has good storage characteristic, does not need ignition and has high reliability. In the actual development process, however, the liquid rocket engine often has unstable combustion phenomenon, which has become one of the biggest problems limiting the development of the high-thrust rocket engine. When unstable combustion occurs, the engine is vibrated slightly, the thrust is reduced, and the performance is reduced; the serious results are that the jetting panel is ablated, the thrust chamber burns through and explodes, the task fails, and serious loss is caused. Unstable combustion can be classified into transversely unstable combustion and longitudinally unstable combustion, wherein the transversely unstable combustion can be further classified into radially unstable combustion and tangentially unstable combustion. When tangential unstable combustion occurs, pressure oscillation of the combustion chamber is coupled with tangential acoustic frequency of the combustion chamber, severe pressure and heat release oscillation are caused, huge periodic heat load is formed on an injection panel and the wall surface of the combustion chamber, the combustion chamber or the injection panel is ablated, and the combustion chamber or the injection panel is extremely destructive. Therefore, the tangential unstable combustion mechanism in the liquid rocket engine needs to be deeply researched, the problem of unstable combustion is thoroughly solved, and the method has great engineering practice significance.
When the tangential unstable combustion of the liquid rocket engine is researched, a full-size rocket engine is generally adopted, and although the condition is closest to the real working condition, the full-size rocket engine has the following defects and needs to be improved:
1. the engine adopting the full-size model has high cost and long period, and needs to consume a large amount 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 unstable combustion problem can not be thoroughly solved.
2. When tangential unstable combustion is researched, the existing model engine is mostly under the normal-pressure working condition, the pressure of a combustion chamber is mostly from 1 atmosphere to several atmospheres, the supercritical condition is not achieved, and the difference from the supercritical pressure in the actual engine is large.
3. In some studies, a detonation, pulse gun was used to artificially excite tangentially unstable combustion, which is very different from the self-excited unstable combustion in practical engines, and it does not have a process in which the pressure oscillation increases to form a limit cycle.
4. The modularization degree is low, the manufacturing and processing are difficult, and the influence of geometric conditions on unstable combustion characteristics is difficult to study.
Disclosure of Invention
The invention aims to solve the technical problem of the prior art and provides an impact type model engine for researching the tangential unstable combustion of a double-liquid-phase propellant, which can be used for researching the high-frequency tangential unstable combustion characteristic of a double-liquid-phase propellant rocket engine, researching the influence of injection working conditions (flow and injection pressure drop) on tangential unstable combustion, the pressure wave propagation characteristic and the unstable combustion generation mechanism and providing guidance for solving the unstable combustion in engineering practice. In addition, the invention can also 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 technical scheme that:
an impact model engine for researching tangential unstable combustion of a double-liquid-phase propellant comprises an oxidant liquid collecting cavity, a propellant partition plate, a jetting panel, a self-excitation cylinder and a combustion chamber.
The oxidant liquid collecting cavity, the injection panel and the combustion chamber are sequentially coaxially, hermetically and detachably connected along the axial direction.
The center of the oxidant liquid collecting cavity is provided with an oxygen collecting cavity.
The top surface of the injection panel is provided with a clapboard groove which is matched with the propellant clapboard in a sealing way.
And a fuel liquid collecting cavity is formed in the injection panel positioned right below the clapboard groove.
And a plurality of fuel spray holes are uniformly distributed on the injection panel which is positioned right below the fuel liquid collecting cavity along the circumferential direction.
Oxidant jet holes with the number equal to that of the fuel jet holes are uniformly distributed on the jet panel 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 combustion chamber.
The fuel spray holes and the corresponding oxidant spray holes are arranged in an intersecting manner, and the intersection points are positioned in the self-excitation circular ring of the combustion chamber.
The center of the bottom of the injection panel positioned in the fuel spray 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-excitation cylinder, the influence of the width and the length of the self-excitation ring of the combustion chamber on self-excitation tangential unstable combustion can be researched.
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 one high-frequency pressure sensor is installed in each high-frequency pressure sensor interface.
At least 2 high-frequency pressure sensor interfaces are distributed on the wall surface of the combustion chamber along the axial direction, and one high-frequency pressure sensor is installed in each high-frequency pressure sensor interface.
And a low-frequency pressure sensor interface is also arranged on the wall surface of the combustion chamber and used for mounting a low-frequency pressure sensor.
The combustion chamber is made of 321 stainless steel materials and can resist 5 Mpa.
The fuel in the fuel collecting cavity is sprayed out through the fuel spray holes, and collides with the oxidant sprayed out through the oxidant spray holes in the self-excited circular ring of the combustion chamber, and spontaneously burns in the combustion chamber, and establishes self-excited unstable combustion to form a pressure oscillation limit ring; wherein the frequency of the self-excited unstable combustion can reach 6700 Hz.
The diameter of each oxidant orifice is 1mm, and the diameter of each fuel orifice is 0.8 mm.
The coaxial seal of the downstream end of combustion chamber can be dismantled and be provided with the Laval spray tube, and through the shrink ratio of adjustment Laval spray tube, can study the influence of Laval spray tube shrink ratio to combustion characteristics.
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 the cost of manpower, material resources and time, can obtain a large amount of experimental data, and deeply studies an unstable combustion mechanism.
(2) The invention can realize self-excited tangential unstable combustion, the chamber pressure of the combustion chamber can reach 5MPa, the supercritical condition can be reached, and the self-excited tangential unstable combustion in the actual combustion chamber is approached to a greater extent. In addition, the impingement design, which naturally has a low stability margin, can produce spontaneous high frequency tangentially unstable combustion.
(3) By adopting a high-degree modular design, the interchangeability of all parts is strong, the influence of the geometrical configuration on high-frequency tangential unstable combustion can be researched by changing the injection panel and the central cylinder, and the replacement can be realized very quickly and conveniently.
(4) And a common 321 stainless steel material is adopted, the processing technology is simpler, and the cost is further saved.
(5) The influence of injection working conditions (flow and injection pressure drop) on tangential unstable combustion, pressure wave propagation characteristics and an unstable combustion generation mechanism can be researched, and guidance is provided for solving the unstable combustion in engineering practice.
(6) The invention can also analyze the thermo-acoustic coupling characteristic when the high-frequency tangential unstable combustion occurs.
Drawings
Fig. 1 shows an explosion diagram of an impact model engine for studying tangentially unstable combustion of a two-liquid phase propellant according to the present invention.
Fig. 2 shows a half-sectional view of fig. 1.
Figure 3 shows a block diagram of the injection panel according to the invention.
Figure 4 shows a cross-sectional view of an insufflating panel with a propellant spacer installed in accordance with the present invention.
Fig. 5 shows the explosion diagram of an impingement model engine without a combustion chamber and laval nozzle according to the present invention.
Fig. 6 shows a structural view of the combustion chamber of the present invention.
Fig. 7 shows a cross-sectional view of the combustion chamber of the present invention.
Figure 8 shows a schematic of the laval nozzle of the present invention.
Figure 9 shows a cross-sectional view of a laval nozzle of the present invention.
Among them are:
10. an oxidant liquid collection chamber; 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 the ring groove;
20. a propellant barrier;
30. an injection panel; 31. a partition plate groove; 32. a fuel collection chamber; 321. a fuel supply passage; 33. a fuel injection hole; 34. spraying an oxidant hole; 35. a threaded post mounting groove; 36. a seal ring;
40. a self-excited 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 portion.
Detailed Description
The present 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 is to be understood that the terms "left side", "right side", "upper part", "lower part", etc., indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and that "first", "second", etc., do not represent an important degree of the component parts, and thus are not to be construed as limiting the present invention. The specific dimensions used in the present example are only for illustrating the technical solution and do not limit the scope of protection of the present invention.
As shown in fig. 1 and 2, the impact type model engine for researching the tangential unstable combustion of the dual-liquid-phase propellant comprises an oxidizer collecting cavity 10, a propellant clapboard 20, a jetting panel 30, a self-excitation 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 sequentially coaxially, hermetically and detachably connected along the axial direction, and preferably 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. Asbestos gaskets and other sealing elements known in the art may also be added between the sealing mating surfaces.
The center of the oxidant liquid collecting cavity is provided with an oxygen collecting cavity. In this embodiment, an oxygen collecting tank 14 with an opening at the bottom is disposed at the center of the bottom of the oxidant liquid collecting chamber, and the oxygen collecting tank is in sealing fit with the top of the injection panel to form an oxygen collecting chamber. Of course, other arrangements known in the art may be used.
In addition, an oxidant supply channel 11 is provided in the center of the top of the oxidant collection chamber for supplying the liquid oxidant to the oxygen collection chamber.
Further, an oxygen high-frequency pressure sensor interface 12 and an oxygen low-frequency pressure sensor interface 13 are 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, the oxygen high-frequency pressure sensor can be used for detecting high-frequency pressure pulsation information in an oxygen collection cavity, and a high-frequency spectrum band is 1 kHz-10 kHz, and the high-frequency spectrum band is similar to the high-frequency band below.
The oxygen low-frequency pressure sensor interface 13 is used for installing an oxygen low-frequency pressure sensor which can be used for detecting low-frequency pressure pulsation information in an oxygen collection cavity, and the low-frequency spectrum band is within 1kHz, and the low-frequency spectrum band is similar to the low-frequency spectrum band.
As shown in fig. 3-5, the top surface of the injection panel is provided with a spacer groove 31 in sealing engagement with a propellant spacer which is preferably sealingly welded therein.
A fuel sump chamber 32 is formed in the injection panel just below the partition plate groove, and is connected to an external fuel supply device through a fuel supply passage 321 formed in the injection panel.
The jetting panel which is positioned right below the fuel liquid collecting cavity is uniformly provided with a plurality of fuel jet holes 33 along the circumferential direction, the diameter of each fuel jet hole is 0.8mm, and the fuel jet holes are inclined towards the axial direction of the jetting panel.
Oxidant jet holes 34 with the same number as the fuel jet holes are uniformly distributed on the jetting panel in the partition plate groove along the circumferential direction, the diameter of each oxidant jet hole is 1mm, and the oxidant jet holes are inclined towards the axis direction deviating from the jetting panel.
Further, a screw post mounting groove 35 is preferably provided at the center of the bottom of the injection panel inside the fuel injection hole.
The present invention employs a highly modular design, and the impact of the impingement nozzle geometry on combustion characteristics (e.g., impingement angle, oxidant and fuel orifice diameters, etc.) can be studied by changing the injector face plate 30.
The combustion chamber is preferably made of 321 stainless steel materials, is a cylinder, has a diameter of preferably 60 cm, and can resist pressure of 5 MPa. 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 in the center of the upstream end of the self-excitation cylinder and can be in threaded connection with the threaded column mounting groove.
For the purpose of rectification, the upstream end of the self-exciting cylinder may be designed to be conical.
A combustion chamber self-excitation circular ring is formed between the self-excitation cylinder and the combustion chamber.
The fuel spray holes and the corresponding oxidant spray holes are arranged in an intersecting manner, and the intersection points are positioned in the self-excitation circular ring of the combustion chamber.
According to the invention, by adjusting the diameter and the length of the self-excitation cylinder, the influence of the width and the length of the self-excitation ring of the combustion chamber on self-excitation tangential unstable combustion can be researched.
Further, the invention can also be used for researching the rotary detonation, such as increasing the diameter of a self-excited cylinder to form a narrow self-excited circular ring of the combustion chamber, so that the invention can be used for researching the rotary detonation characteristics of the two-component propellant and the relation between the tangential unstable combustion and the rotary detonation.
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 one high-frequency pressure sensor is installed in each high-frequency pressure sensor interface. The high-frequency pressure sensors 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 distributed on the wall surface of the combustion chamber along the axial direction, and one high-frequency pressure sensor is installed in each high-frequency pressure sensor interface. The high-frequency pressure sensor arranged along the axial direction can detect high-frequency longitudinally unstable combustion in the combustion chamber.
Further, a low-frequency pressure sensor interface 52 is arranged on the wall surface of the combustion chamber and used for installing a low-frequency pressure sensor. The low-frequency pressure sensor can be used for detecting low-frequency pressure pulsation information in the combustion chamber.
Furthermore, the combustion chamber may also be optically diagnosed by optical windowing (not shown in the figures).
The laval nozzle (also known as a nozzle) accelerates hot gases in the combustion chamber to sonic velocity at the throat 61, forming an acoustic cutoff. The invention can research the influence of the shrinkage ratio of the Laval nozzle on the combustion characteristic by adjusting the shrinkage ratio of the Laval nozzle. Alternatively, the laval nozzle may be modified to be a plug nozzle.
The fuel in the fuel liquid collecting cavity is sprayed out through the fuel spray holes and collides with the oxidant sprayed out through the oxidant spray holes in the self-excited circular ring of the combustion chamber, the propellant is atomized, ignition is not needed due to the characteristics of the self-ignited propellant, the oxidant and the fuel spontaneously combust in the combustion chamber when meeting, the self-excited unstable combustion is quickly established, a pressure oscillation limit ring is formed, and the unstable combustion characteristics are researched; the combusted gas is discharged through the Laval nozzle, and acoustic cut-off is realized at the throat part.
Since unstable combustion can be established quickly in a very short time (< 30 ms), the duration of the experiment is about 1 s. To simplify the model engine construction, the combustion chamber and nozzle are heat sink cooled, but water cooled or regenerative cooling can also be achieved by design.
The applicant has already completed model engine design at present, and carries out numerical simulation verification on the invention to discover that: the invention can realize self-excitation high-frequency tangential unstable combustion, and the frequency is up to 6700 Hz.
Although the preferred embodiments of the present invention have been described in detail, the present invention is not limited to the details of the embodiments, and various equivalent modifications can be made within the technical spirit of the present invention, and the scope of the present invention is also within the scope of the present invention.
Claims (10)
1. The utility model provides a research biliquid phase propellant tangential unstable combustion's impacted style model engine which characterized in that: comprises an oxidant liquid collecting cavity, a propellant clapboard, a jetting panel, a self-excitation cylinder and a combustion chamber;
the oxidant liquid collecting cavity, the injection panel and the combustion chamber are sequentially coaxially, hermetically 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 clapboard groove which is in sealing fit with the propellant clapboard;
a fuel liquid collecting cavity is formed in the injection panel which is positioned right below the clapboard groove;
a plurality of fuel spray holes are uniformly distributed on the injection panel which is positioned right below the fuel liquid collecting cavity along the circumferential direction;
oxidant jet holes with the number equal to that of the fuel jet holes are uniformly distributed on the jet panel 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 combustion chamber;
the fuel spray holes and the corresponding oxidant spray holes are arranged in an intersecting manner, and the intersection points are positioned in the self-excitation circular ring of the combustion chamber.
2. The impact type model engine for researching tangential unstable combustion of the double-liquid-phase propellant is characterized in that: the center of the bottom of the injection panel positioned in the fuel spray 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.
3. The impact model engine for researching tangential unstable combustion of the double-liquid-phase propellant as claimed in claim 2, is characterized in that: by adjusting the diameter and the length of the self-excitation cylinder, the influence of the width and the length of the self-excitation ring of the combustion chamber on self-excitation tangential unstable combustion can be researched.
4. The impact type model engine for researching tangential unstable combustion of the double-liquid-phase propellant is characterized in that: 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 a high-frequency pressure sensor is installed in each high-frequency pressure sensor interface.
5. The impact model engine for researching tangential unstable combustion of the double-liquid-phase propellant according to claim 4 is characterized in that: at least 2 high-frequency pressure sensor interfaces are distributed on the wall surface of the combustion chamber along the axial direction, and one high-frequency pressure sensor is installed in each high-frequency pressure sensor interface.
6. The impact type model engine for researching tangential unstable combustion of the double-liquid-phase propellant according to claim 4 or 5 is characterized in that: and a low-frequency pressure sensor interface is also arranged on the wall surface of the combustion chamber and used for mounting a low-frequency pressure sensor.
7. The impact type model engine for researching tangential unstable combustion of the double-liquid-phase propellant is characterized in that: the combustion chamber is made of 321 stainless steel materials and can resist 5 Mpa.
8. The impact model engine for researching tangential unstable combustion of the double-liquid-phase propellant as claimed in claim 1 or 7, is characterized in that: the fuel in the fuel collecting cavity is sprayed out through the fuel spray holes, and collides with the oxidant sprayed out through the oxidant spray holes in the self-excited circular ring of the combustion chamber, and spontaneously burns in the combustion chamber, and establishes self-excited unstable combustion to form a pressure oscillation limit ring; wherein the frequency of the self-excited unstable combustion can reach 6700 Hz.
9. The impact model engine for researching tangential unstable combustion of the double-liquid-phase propellant as claimed in claim 1, is characterized in that: the diameter of each oxidant orifice is 1mm, and the diameter of each fuel orifice is 0.8 mm.
10. The impact model engine for researching tangential unstable combustion of the double-liquid-phase propellant as claimed in claim 1, is characterized in that: the coaxial seal of the downstream end of combustion chamber can be dismantled and be provided with the Laval spray tube, and through the shrink ratio of adjustment Laval spray tube, can study the influence of Laval spray tube shrink ratio to combustion characteristics.
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 |
Publications (2)
| Publication Number | Publication Date |
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| CN114607526A true CN114607526A (en) | 2022-06-10 |
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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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