CN114876669B - Coaxial model engine for researching tangential unstable combustion of rocket engine - Google Patents
Coaxial model engine for researching tangential unstable combustion of rocket engine Download PDFInfo
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- CN114876669B CN114876669B CN202210342725.3A CN202210342725A CN114876669B CN 114876669 B CN114876669 B CN 114876669B CN 202210342725 A CN202210342725 A CN 202210342725A CN 114876669 B CN114876669 B CN 114876669B
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 143
- 238000002347 injection Methods 0.000 claims abstract description 27
- 239000007924 injection Substances 0.000 claims abstract description 27
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 31
- 239000001301 oxygen Substances 0.000 claims description 31
- 229910052760 oxygen Inorganic materials 0.000 claims description 31
- 239000007800 oxidant agent Substances 0.000 claims description 30
- 239000000446 fuel Substances 0.000 claims description 27
- 238000010008 shearing Methods 0.000 claims description 25
- 230000001590 oxidative effect Effects 0.000 claims description 24
- 238000007789 sealing Methods 0.000 claims description 22
- 239000007921 spray Substances 0.000 claims description 21
- 238000011144 upstream manufacturing Methods 0.000 claims description 21
- 238000003825 pressing Methods 0.000 claims description 18
- 239000003380 propellant Substances 0.000 claims description 15
- 239000007788 liquid Substances 0.000 claims description 11
- 238000005192 partition Methods 0.000 claims description 9
- 239000007789 gas Substances 0.000 claims description 7
- 230000009977 dual effect Effects 0.000 claims description 5
- 238000009434 installation Methods 0.000 claims description 4
- 238000005507 spraying Methods 0.000 claims description 3
- 238000011160 research Methods 0.000 description 6
- 238000001228 spectrum Methods 0.000 description 6
- 230000004888 barrier function Effects 0.000 description 4
- 230000010349 pulsation Effects 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 238000005474 detonation Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 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
- 238000002474 experimental method Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000010355 oscillation Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 229910001220 stainless steel Inorganic materials 0.000 description 2
- 239000010935 stainless steel Substances 0.000 description 2
- 239000010425 asbestos Substances 0.000 description 1
- 238000000889 atomisation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 229910052895 riebeckite Inorganic materials 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
- 230000009897 systematic effect Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- 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
-
- 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
- F02K9/97—Rocket nozzles
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
The invention discloses a coaxial model engine for researching tangential unstable combustion of a rocket engine, which comprises a plurality of double-component injectors, and an injection panel and a combustion chamber which are coaxially and detachably connected in sequence along the axial direction; a plurality of double-component injectors are uniformly distributed along the circumferential direction of the injection panel; the center of the bottom surface of the injection panel is coaxially provided with a combustion chamber center cylinder extending into the combustion chamber, and a combustion chamber circular ring is formed between the combustion chamber center cylinder and the inner wall surface of the combustion chamber; the combustion chamber ring can realize self-exciting tangential unstable combustion in the combustion chamber. According to the invention, the relationship between the tangential unstable combustion of the rocket engine and the width and length of the circular ring of the combustion chamber is researched and studied by changing the diameter and the length of the central cylinder; in addition, the relationship between the tangentially unstable combustion and the rotational knocking of the rocket engine can be studied.
Description
Technical Field
The invention relates to a model engine, in particular to a coaxial model engine for researching tangential unstable combustion of a rocket engine.
Background
In the next decades that can be foreseen, chemical reaction-based rocket engines remain the main power tool for human entry into and exit from space. Currently, rocket engines are widely used in various spacecrafts (e.g., primary rocket engines, gas generators, rocket engine movers, satellite attitude and orbit control engines, missile power systems, and the like). But nearly all rocket engine development processes encounter varying degrees of unstable combustion. Unstable combustion has become one of the key factors limiting the development of high thrust rocket engines. Unstable combustion can be classified into longitudinally unstable combustion and transversely unstable combustion from the vibration mode. Wherein the transverse unstable combustion comprises radial vibration mode and tangential vibration mode. When high-frequency tangential unstable combustion occurs, huge pressure oscillation and combustion chamber heat release pulsation are accompanied, and engine vibration is caused by light weight, so that the thrust is reduced, and the performance is reduced; and if the weight is heavy, the injection panel is ablated, the thrust chamber burns through and explodes, and the task fails. Injection atomization is one of the important factors affecting unstable combustion, and different nozzle forms and nozzle geometry can greatly affect the combustion stability characteristics of rocket engines. Therefore, the intensive research of the tangential unstable combustion of the rocket engine and the response rule of the rocket engine to the nozzle form and the nozzle geometric parameters has great practical engineering significance. The tangential unstable combustion has a rotation wave mode and a standing wave mode, wherein the rotation wave mode and the rotation knocking have a certain similarity, but the academic world has no systematic experimental research on the relationship between the rotation wave mode and the rotation knocking, and has no effective experimental tool for researching the relationship between the rotation wave mode and the rotation knocking.
In researching the tangentially unstable combustion of a liquid rocket engine, a full-size rocket engine is usually adopted, and although the condition is closest to the actual working condition, the following defects still exist, and the improvement is needed:
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 cannot be windowed, the pressure measuring interface cannot be opened, the pressure oscillation characteristic and the flame propagation characteristic in the combustion chamber cannot be studied, and the obtained data are very limited.
2. Most of the existing model engines are cylindrical model engines with large length-diameter ratio, and only longitudinal unstable combustion can be studied, but transverse unstable combustion cannot be studied.
3. In some researches, the artificial excitation of unstable combustion by using explosive charges and pulse guns is very different from the self-excited unstable combustion in a combustion chamber and can be directly analogized.
4. When a model engine is adopted to study tangential unstable combustion, the pressure of a model engine chamber is often too low (usually a few atmospheres), a supercritical condition is not achieved, and the state of a real combustion chamber cannot be simulated.
5. The conventional model engine needs to replace the whole injection panel when researching the influence of the nozzle configuration, is complex to operate, and needs to process various injection panels, so that economic and time waste is caused.
Disclosure of Invention
The invention aims to solve the technical problem of the prior art, and provides a coaxial model engine for researching the tangential unstable combustion of a rocket engine, which can realize the self-excited tangential unstable combustion, wherein two-component injectors are distributed on an injection panel in a single ring.
In order to solve the technical problems, the invention adopts the following technical scheme:
a coaxial model engine for researching tangential unstable combustion of rocket engine comprises a plurality of two-component injectors, and an injection panel and a combustion chamber which are coaxially and sequentially sealed and detachably connected along the axial direction.
The two-component injectors are uniformly distributed along the circumferential direction of the injection panel.
The center of the bottom surface of the injection panel is coaxially provided with a combustion chamber center cylinder extending into the combustion chamber, and a combustion chamber circular ring is formed between the combustion chamber center cylinder and the inner wall surface of the combustion chamber; the combustion chamber ring can realize self-exciting tangential unstable combustion in the combustion chamber.
By adjusting the diameter and the length of the central cylinder of the combustion chamber, the influence of the width and the length of the circular ring of the combustion chamber on self-excited tangential unstable combustion can be studied.
The device also comprises an oxidant cavity, a nozzle pressing plate and a propellant partition plate, wherein the oxidant cavity, the nozzle pressing plate and the propellant partition plate are arranged at the upstream of the injection panel in sequence along the axial direction.
The oxidant cavity and the nozzle pressing plate are both in coaxial sealing and detachable connection with the injection panel.
The nozzle pressing plate is uniformly provided with inner nozzle mounting holes with the same number as that of the two-component injector along the circumferential direction.
The propellant partition plate is uniformly provided with nozzle perforations with the same number as the two-component injector along the circumferential direction.
Nozzle mounting holes with the same number as the two-component injectors are uniformly distributed on the injection panel along the circumferential direction; each nozzle mounting hole comprises a ring separating groove, a fuel cavity and a spray hole which are sequentially distributed along the axial direction and are mutually communicated.
The propellant partition is coaxially and hermetically arranged in the partition groove, and the top surface is in pressing contact with the nozzle pressing plate.
Each dual-component injector is axially arranged and sequentially installed in the corresponding inner nozzle installation hole, nozzle perforation and nozzle installation hole.
Each dual component injector is a coaxial shear nozzle.
The in-line shearing nozzle comprises an oxygen shearing nozzle; the oxygen shearing nozzles are coaxially inserted into spray holes corresponding to the nozzle mounting holes in the spraying panel.
A fuel shearing circular seam is formed between the outer wall surface of the oxygen shearing nozzle and the inner wall surface of the corresponding spray hole; the downstream end of the oxygen shear nozzle is retracted relative to the orifice, thereby forming a shear retraction chamber.
Each dual component injector is a coaxial swirl nozzle.
The coaxial swirl nozzle includes an inner nozzle and an outer nozzle.
The center of the inner nozzle is provided with an inner center circulation communicated with the oxidant cavity; the inner nozzle comprises a large cylindrical section, a middle cylindrical section and a small cylindrical section which are sequentially and integrally arranged along the axial direction and gradually reduced in outer diameter; wherein, big cylinder section installs in the interior nozzle mounting hole of nozzle clamp plate.
The outer nozzle is coaxially sleeved on the periphery of the middle cylindrical section and the small cylindrical section of the inner nozzle.
The outer wall surface of the outer nozzle is connected with the spray hole in a sealing way.
The inner wall surface of the outer nozzle is in sealing connection with the outer wall surface of the middle cylindrical section, and an outer annular gap is formed between the inner wall surface of the outer nozzle and the outer wall surface of the small cylindrical section; the outer circumferential seam is communicated with the fuel cavity through an outer fuel passage.
The downstream end of the small cylindrical section is retracted relative to the outer nozzle to form a swirl retraction chamber.
Each coaxial cyclone nozzle is a liquid-liquid double cyclone nozzle.
An inner flow chamber is arranged at the upstream of the inner central flow passage, and an inner plug is arranged at the upstream end of the inner flow chamber; the internal flow chamber is communicated with the oxidant cavity through a plurality of internal cutting holes which are uniformly distributed along the circumferential direction of the internal flow chamber.
The outer fuel channel is a plurality of external tangential holes which are uniformly distributed along the circumferential direction of the outer nozzle.
Each coaxial swirl nozzle is a liquid-centered gas shear nozzle.
An inner flow chamber is arranged at the upstream of the inner central flow passage, and an inner plug is arranged at the upstream end of the inner flow chamber; the internal flow chamber is communicated with the oxidant cavity through a plurality of internal cutting holes which are uniformly distributed along the circumferential direction of the internal flow chamber.
The outer fuel channel is a plurality of outer radial holes uniformly distributed along the circumference of the outer nozzle.
Each coaxial swirl nozzle is a gas-centered liquid swirl nozzle.
The upstream end of the inner central runner is directly communicated with the oxidant cavity.
The outer fuel channel is a plurality of external tangential holes which are uniformly distributed along the circumferential direction of the outer nozzle.
The periphery of the large cylindrical section is provided with a limiting shaft shoulder for limiting the axial position of the inner nozzle.
The downstream end of the combustion chamber is provided with the spray pipe in a detachable manner in a coaxial sealing manner, and the influence of the shrinkage ratio of the spray pipe on the combustion characteristic can be studied by adjusting the shrinkage ratio of the spray pipe.
The invention has the following beneficial effects:
1. the cross section of the combustion chamber is cylindrical, and the modularized combustion chamber center cylinder is designed, so that the combustion chamber has a low stability margin, and spontaneous tangential unstable combustion can be generated. The relationship between the tangential unstable combustion of the rocket engine and the width and length of the circular ring of the combustion chamber is researched and studied by changing the diameter and the length of the central cylinder; in addition, the relationship between the tangentially unstable combustion and the rotational knocking of the rocket engine can be studied. If the diameter of the central cylinder of the combustion chamber is increased, a very narrow combustion chamber circular ring is formed, so that the combustion chamber circular ring can be used for researching the rotation knocking characteristic of the two-component propellant and the relationship between tangential unstable combustion and rotation knocking.
2. The invention can analyze thermo-acoustic coupling characteristics when unstable combustion occurs, and research the influence of injection working conditions (flow and injection pressure drop) on transverse unstable combustion. The impact of injector geometry (e.g., retract chamber length, nozzle diameter, nozzle length, orifice diameter, circumferential gap width, etc.) on combustion characteristics is readily studied by modular design.
3. The invention can conveniently replace the dual-component injector through the modularized design, and can study the influence on tangential unstable combustion in the form of injectors such as a coaxial shearing injector, a liquid-liquid dual-cyclone injector, a liquid center type gas coaxial shearing injector, a gas center type liquid cyclone injector and the like.
4. The invention researches the influence of nozzle geometric conditions (such as the retraction length, the diameter of the spray hole, the number of tangential holes and the like) on combustion characteristics and tangential unstable combustion thereof by changing the nozzle component.
5. The invention can open the window of the combustion chamber, visually study the pressure wave propagation characteristic and the unstable combustion generation mechanism through the flow field, and provide guidance for solving the unstable combustion in engineering practice.
6. The invention can research the flame, pressure wave and thermo-acoustic coupling characteristics, deeply analyze the unstable combustion mechanism and obtain abundant experimental data. The chamber pressure of the combustion chamber is higher (can reach 5 Mpa) to reach a supercritical condition, and can be similar to the chamber pressure of a rocket engine to a certain extent.
Drawings
FIG. 1 shows an exploded view of a coaxial model engine of the present invention for studying tangentially unstable combustion of a rocket engine.
Fig. 2 shows a cross-sectional view of fig. 1.
FIG. 3 shows a cross-sectional view of a coaxial model engine (without the combustion chamber and nozzle) using a coaxial swirl nozzle.
FIG. 4 shows a cross-sectional view of the injection panel structure with a two-component injector and a central cylinder of the combustion chamber mounted.
Fig. 5 shows an exploded view of fig. 3.
FIG. 6 shows a cross-sectional view of a coaxial model engine (without combustion chamber and nozzle) using a coaxial shear nozzle.
Fig. 7 shows a schematic perspective view of the coaxial swirl nozzle of the present invention.
FIG. 8 shows a cross-sectional view of a coaxial swirl nozzle of the present invention as a liquid-liquid dual swirl nozzle.
Fig. 9 shows a cross-sectional view of a coaxial swirl nozzle of the present invention as a liquid-centered gas shearing nozzle.
Fig. 10 shows a cross-sectional view of a coaxial swirl nozzle of the present invention as a gas-centered liquid swirl nozzle.
Fig. 11 shows a schematic structural view of the coaxial shear nozzle of the present invention.
Fig. 12 shows a cross-sectional view of a coaxial shear nozzle in accordance with the present invention.
Fig. 13 shows a schematic view of the structure of the combustion chamber in the present invention.
FIG. 14 shows a cross-sectional view of a spout in accordance with the present invention.
The method comprises the following steps:
10. an oxidant chamber; 11. an oxidant supply conduit; 12. an oxygen high frequency pressure sensor interface; 13. an oxygen low frequency pressure sensor interface; 14. sealing ring grooves;
20. a nozzle platen; 21. an inner nozzle mounting hole; 22. a seal ring;
30. a two-component injector;
31. a coaxial shear nozzle; 311. an oxygen shear nozzle; 311a. Oxygen central passage; 311b, flaring; 311c, shaft shoulders; 311d, sealing grooves; 312. cutting the circumferential seam by fuel; 313. a shear retraction chamber;
32. a coaxial swirl nozzle;
321. an inner nozzle; 321a, an inner central runner; 321b, an inner swirl chamber; 321c, an inner plug; 321d, internal tangential holes; 321e, inner chamfering; 321f, limiting the shaft shoulder; 321g, an inner axial seal groove; 321h, large cylindrical section; 321i, a middle cylindrical section; 321j. Small cylindrical sections;
322. an outer nozzle; 322a. An outward facing aperture; 322b. Outer radial holes; 322c, an outer central flow passage; 322d, an outer upper axial seal groove; 322e, an outer lower axial seal groove;
323. an outer circumferential seam; 324. a swirl retraction chamber;
40. a propellant barrier; 41. perforating a nozzle;
50. injecting a panel; 51. a cylinder mounting groove; 521, a ring separating groove; 522. a fuel chamber; 522a. Fuel supply lines;
60. a combustion chamber central cylinder; 61. a stud;
70. a combustion chamber; 71. a high frequency pressure sensor interface; 72. a low frequency pressure sensor interface;
80. a spray pipe; 81. a nozzle 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, a coaxial model engine for studying tangentially unstable combustion of a rocket engine comprises an oxidizer 10, a nozzle platen 20, a plurality of two-component injectors 30, a propellant barrier 40, an injection panel 50, a combustion chamber central cylinder 60, a combustion chamber 70 and a nozzle 80.
The oxidant chamber 10, the nozzle platen 20, the injector face plate 50, the combustion chamber 70 and the lance 80 are axially coaxially and sealingly detachably connected in sequence, preferably by a threaded flange connection. The specific sealing mode is preferably as follows: between the mating surfaces, a seal ring groove 14 and a seal ring 22 are provided which are in sealing engagement with each other as shown in fig. 3. 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.
In the embodiment, an oxygen collecting groove with an opening at the bottom is arranged at the center of the bottom surface of the oxidant cavity, and the oxygen collecting groove is in sealing fit with the top surface of the nozzle pressing plate to form a sealed oxidant cavity. Of course, other arrangements known in the art may be used.
As shown in fig. 3 to 5, an oxidizer supply pipe 11 is provided at the top center of the oxidizer chamber for supplying the oxidizer to the oxidizer chamber.
Further, an oxygen high frequency pressure sensor interface 12 and an oxygen low frequency pressure sensor interface 13 are also provided at the top of the oxidant chamber.
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 oxidant 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 oxidant cavity, wherein the low-frequency spectrum is within 1kHz, and the low-frequency spectrum is similar to the low-frequency spectrum below.
The nozzle pressing plate is uniformly provided with inner nozzle mounting holes 21 with the same number as the two-component injector along the circumferential direction.
The propellant barrier is circumferentially uniformly provided with nozzle perforations 41 equal in number to the two-component injectors.
The injection panel is uniformly provided with nozzle mounting holes 52 with the same number as the two-component injectors along the circumferential direction; each nozzle mounting hole includes a diaphragm groove 521, a fuel chamber 522, and a nozzle hole 523, which are sequentially arranged in the axial direction and communicate with each other.
The propellant diaphragm is mounted in the diaphragm groove in a coaxial seal (preferably a seal weld) with the top surface in pressing contact with the nozzle platen.
The fuel chamber is connected to an external fuel supply via a fuel supply conduit 522a provided on the injector panel.
The two-component injectors are uniformly distributed along the circumferential direction of the injection panel, are axially distributed, and are sequentially arranged in the corresponding inner nozzle mounting holes, the nozzle perforations and the nozzle mounting holes.
The dual component injector of the present invention is preferably a coaxial shear nozzle or a coaxial swirl nozzle.
A. The two-component injector is a coaxial shearing nozzle
As shown in fig. 6, 11 and 12, the in-line shearing nozzle 31 includes an oxygen shearing nozzle 311; the oxygen shearing nozzles are coaxially inserted into spray holes corresponding to the nozzle mounting holes in the spraying panel.
A fuel shearing circumferential gap 312 is formed between the outer wall surface of the oxygen shearing nozzle and the inner wall surface of the corresponding spray hole; the downstream end of the oxygen shear nozzle is retracted relative to the orifice, thereby forming a shear retraction chamber 313.
The center of the oxygen shearing nozzle is provided with an oxygen central passage 311a, the upstream end of which is preferably provided with a flare 311b.
The middle part of the outer wall of the oxygen shearing nozzle is preferably provided with a shaft shoulder 311c for positioning the axial position of the oxygen shearing nozzle. The middle part of the outer wall of the shaft shoulder is preferably provided with a sealing groove 311d for sealing and matching the outer wall of the shaft shoulder with the nozzle perforation 41, the bottom of the shaft shoulder is also sealed and limited and installed in the nozzle perforation 41, and the top of the shaft shoulder is in pressing fit with the nozzle pressing plate.
The present invention was based on coaxial shear nozzles, using a methane/oxygen propellant combination for experiments. In the experiment, high-frequency tangential unstable combustion is observed, the frequency is up to 3000Hz, and the purpose of the invention is achieved.
B. The two-component injector is a coaxial swirl nozzle
As shown in fig. 3, 4, 5, 7-10, the coaxial swirl nozzle includes an inner nozzle 321 and an outer nozzle 322.
The center of the inner nozzle is provided with an inner center flow 321a communicated with the oxidant cavity; the inner nozzle comprises a large cylindrical section 321h, a middle cylindrical section 321i and a small cylindrical section 321j which are sequentially and integrally arranged along the axial direction and gradually reduced in outer diameter; wherein the middle of the large cylindrical section is preferably mounted in the inner nozzle mounting hole of the nozzle pressing plate, and the bottom of the large cylindrical section is preferably mounted in the nozzle penetrating hole 41 in a sealing way through the inner axial sealing groove 321g.
The outer wall of the large cylinder at the top of the inner axial seal groove 321g is also preferably provided with a limit shoulder 321f, preferably on top of the propellant barrier, to locate the axial position of the inner nozzle.
The outer nozzle is coaxially sleeved on the outer periphery of the middle cylindrical section and the small cylindrical section of the inner nozzle, and is provided with an outer center flow passage 322c.
The top outer wall surface of the outer nozzle is preferably in sealing engagement with the nozzle bore 41 through an outer upper axial seal groove 322d and a seal ring embedded therein, and the bottom outer wall surface of the outer nozzle is preferably in sealing engagement with the nozzle bore through an outer lower axial seal groove 322e and a seal ring embedded therein.
The inner wall surface of the outer nozzle is in sealing connection with the outer wall surface of the middle cylindrical section, and an outer circumferential seam 323 is formed between the inner wall surface of the outer nozzle and the outer wall surface of the small cylindrical section; the outer circumferential seam is communicated with the fuel cavity through an outer fuel passage.
The downstream end of the small cylindrical section is retracted relative to the outer nozzle to form a swirl retraction chamber 324.
The coaxial swirl nozzle described above has the following three preferred embodiments.
Example 1 the coaxial swirl nozzle is a liquid-liquid double swirl nozzle
As shown in fig. 8, an inner flow chamber 321b is arranged at the upstream of the inner central flow channel, and an inner plug 321c is arranged at the upstream end of the inner flow chamber; the inner flow chamber communicates with the oxidizer chamber through a plurality of inner cut holes 31d uniformly distributed along the circumferential direction thereof.
The outer fuel passage is a plurality of outer tangential holes 322a uniformly distributed along the circumference of the outer nozzle.
Example 2 the coaxial swirl nozzle was a liquid-centered gas shear nozzle
As shown in fig. 9, an inner flow chamber is arranged at the upstream of the inner central flow channel, and an inner plug is arranged at the upstream end of the inner flow chamber; the internal flow chamber is communicated with the oxidant cavity through a plurality of internal cutting holes which are uniformly distributed along the circumferential direction of the internal flow chamber.
The outer fuel passage is a plurality of outer radial holes 322b uniformly distributed along the circumference of the outer nozzle.
Example 3 the coaxial swirl nozzle was a gas-centered liquid swirl nozzle
The upstream end of the inner central flow passage is preferably provided with an inner chamfer 321e and communicates directly with the oxidant chamber.
The outer fuel channel is a plurality of external tangential holes which are uniformly distributed along the circumferential direction of the outer nozzle.
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 central cylinder of the combustion chamber is coaxially arranged at the upstream end of the combustion chamber, and a stud 61 is preferably coaxially arranged at the center of the upstream end of the central cylinder of the combustion chamber and can be in threaded connection with a cylinder mounting groove 51 arranged at the center of the bottom of the injection panel.
For ease of rectification, the upstream end of the central cylinder of the combustion chamber may be conically shaped.
A combustion chamber circular ring is formed between the combustion chamber central cylinder and the combustion chamber inner wall surface; the combustion chamber ring can realize self-exciting tangential unstable combustion in the combustion chamber.
By adjusting the diameter and the length of the central cylinder of the combustion chamber, the influence of the width and the length of the circular ring of the combustion chamber on self-excited tangential unstable combustion can be studied.
Further, the invention can also be used to study rotational detonation, such as increasing the diameter of the central cylinder of the combustion chamber to form a very narrow combustion chamber ring, thereby being capable of being used to study the rotational detonation characteristics of a two-component propellant and the relationship between tangentially unstable combustion and rotational detonation.
At least 2 high-frequency pressure sensor interfaces 71 are circumferentially distributed on the wall surface of the combustion chamber corresponding to the combustion chamber ring, and each high-frequency pressure sensor interface is internally provided with a 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 72 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 lance 80 accelerates the hot gases in the combustion chamber to a sonic velocity at the lance throat 81, creating an acoustic cutoff. The invention can study the influence of the shrinkage ratio of the spray pipe on the combustion characteristic by adjusting the shrinkage ratio of the spray pipe. Alternatively, the nozzle may be modified to be a plug nozzle.
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 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 (8)
1. A coaxial model engine for researching tangential unstable combustion of a rocket engine is characterized in that: comprises a plurality of double-component injectors, and an injection panel and a combustion chamber which are coaxially and detachably connected in sequence along the axial direction;
a plurality of double-component injectors are uniformly distributed along the circumferential direction of the injection panel in a single ring;
each dual-component injector is a coaxial shearing nozzle or a coaxial rotational flow nozzle; by replacing the dual-component injector, the influence on tangential unstable combustion of the coaxial shearing nozzle and the coaxial cyclone nozzle can be studied;
the center of the bottom surface of the injection panel is coaxially provided with a combustion chamber center cylinder extending into the combustion chamber, and a combustion chamber circular ring is formed between the combustion chamber center cylinder and the inner wall surface of the combustion chamber; the combustion chamber ring can realize self-exciting tangential unstable combustion in the combustion chamber;
the influence of the width and the length of the circular ring of the combustion chamber on self-excited tangential unstable combustion can be studied by adjusting the diameter and the length of the central cylinder of the combustion chamber;
the device also comprises an oxidant cavity, a nozzle pressing plate and a propellant partition plate which are positioned at the upstream of the injection panel and are sequentially distributed along the axial direction;
the oxidant cavity and the nozzle pressing plate are both in coaxial sealing and detachable connection with the injection panel;
the nozzle pressing plate is uniformly provided with inner nozzle mounting holes with the same number as that of the two-component injector along the circumferential direction;
nozzle perforations with the same number as that of the two-component injector are uniformly distributed on the propellant partition plate along the circumferential direction;
nozzle mounting holes with the same number as the two-component injectors are uniformly distributed on the injection panel along the circumferential direction; each nozzle mounting hole comprises a ring separating groove, a fuel cavity and a spray hole which are sequentially distributed along the axial direction and are mutually communicated;
the propellant partition board is coaxially and hermetically arranged in the partition ring groove, and the top surface is in pressing contact with the nozzle pressing plate;
each dual-component injector is axially arranged and sequentially installed in the corresponding inner nozzle installation hole, nozzle perforation and nozzle installation hole.
2. The coaxial model engine for studying tangentially unstable combustion of rocket engine according to claim 1, wherein: each dual component injector is a coaxial shear nozzle;
the in-line shearing nozzle comprises an oxygen shearing nozzle; the oxygen shearing nozzles are coaxially inserted into spray holes corresponding to the nozzle mounting holes in the spraying panel;
a fuel shearing circular seam is formed between the outer wall surface of the oxygen shearing nozzle and the inner wall surface of the corresponding spray hole; the downstream end of the oxygen shear nozzle is retracted relative to the orifice, thereby forming a shear retraction chamber.
3. The coaxial model engine for studying tangentially unstable combustion of rocket engine according to claim 1, wherein: each dual-component injector is a coaxial swirl nozzle;
the coaxial swirl nozzle comprises an inner nozzle and an outer nozzle;
the center of the inner nozzle is provided with an inner center runner communicated with the oxidant cavity; the inner nozzle comprises a large cylindrical section, a middle cylindrical section and a small cylindrical section which are sequentially and integrally arranged along the axial direction and gradually reduced in outer diameter; the large cylindrical section is arranged in an inner nozzle mounting hole of the nozzle pressing plate;
the outer nozzle is coaxially sleeved on the peripheries of the middle cylindrical section and the small cylindrical section of the inner nozzle;
the outer wall surface of the outer nozzle is connected with the spray hole in a sealing way;
the inner wall surface of the outer nozzle is in sealing connection with the outer wall surface of the middle cylindrical section, and an outer annular gap is formed between the inner wall surface of the outer nozzle and the outer wall surface of the small cylindrical section; the outer annular seam is communicated with the fuel cavity through an outer fuel channel;
the downstream end of the small cylindrical section is retracted relative to the outer nozzle to form a swirl retraction chamber.
4. A coaxial model engine for studying tangentially unstable combustion of a rocket engine according to claim 3, characterized in that: each coaxial cyclone nozzle is a liquid-liquid double-cyclone nozzle;
an inner flow chamber is arranged at the upstream of the inner central flow passage, and an inner plug is arranged at the upstream end of the inner flow chamber; the internal flow chamber is communicated with the oxidant cavity through a plurality of internal cutting holes uniformly distributed along the circumferential direction of the internal flow chamber;
the outer fuel channel is a plurality of external tangential holes which are uniformly distributed along the circumferential direction of the outer nozzle.
5. A coaxial model engine for studying tangentially unstable combustion of a rocket engine according to claim 3, characterized in that: each coaxial swirl nozzle is a liquid-centered gas shearing nozzle;
an inner flow chamber is arranged at the upstream of the inner central flow passage, and an inner plug is arranged at the upstream end of the inner flow chamber; the internal flow chamber is communicated with the oxidant cavity through a plurality of internal cutting holes uniformly distributed along the circumferential direction of the internal flow chamber;
the outer fuel channel is a plurality of outer radial holes uniformly distributed along the circumference of the outer nozzle.
6. A coaxial model engine for studying tangentially unstable combustion of a rocket engine according to claim 3, characterized in that: each coaxial swirl nozzle is a gas-centered liquid swirl nozzle;
the upstream end of the inner central runner is directly communicated with the oxidant cavity;
the outer fuel channel is a plurality of external tangential holes which are uniformly distributed along the circumferential direction of the outer nozzle.
7. A coaxial model engine for studying tangentially unstable combustion of a rocket engine according to claim 3, characterized in that: the periphery of the large cylindrical section is provided with a limiting shaft shoulder for limiting the axial position of the inner nozzle.
8. The coaxial model engine for studying tangentially unstable combustion of rocket engine according to claim 1, wherein: the downstream end of the combustion chamber is provided with the spray pipe in a detachable manner in a coaxial sealing manner, and the influence of the shrinkage ratio of the spray pipe on the combustion characteristic can be studied by adjusting the shrinkage ratio of the spray pipe.
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