CN114645801A - Rectangular model rocket engine capable of generating self-excitation transverse high-frequency unstable combustion - Google Patents
Rectangular model rocket engine capable of generating self-excitation transverse high-frequency unstable combustion Download PDFInfo
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- CN114645801A CN114645801A CN202210259705.XA CN202210259705A CN114645801A CN 114645801 A CN114645801 A CN 114645801A CN 202210259705 A CN202210259705 A CN 202210259705A CN 114645801 A CN114645801 A CN 114645801A
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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
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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
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
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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
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
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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
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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- 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)
- Testing Of Engines (AREA)
Abstract
The invention discloses a rectangular model rocket engine capable of generating self-excitation transverse high-frequency unstable combustion, which comprises a nozzle assembly, an oxidant chamber, a jetting panel, a combustion chamber and a tail nozzle, wherein the oxidant chamber, the jetting panel, the combustion chamber and the tail nozzle are sequentially and coaxially arranged along a jetting direction and are rectangular; the nozzle assembly comprises a nozzle fixing panel and nozzles with the number equal to that of the fuel spray holes; an annular fuel injection annular seam is formed between each nozzle and the corresponding fuel spray hole; the combustion chamber is provided with an ignition interface, a transverse high-frequency pressure monitoring port and a longitudinal high-frequency pressure monitoring port; the transverse high-frequency pressure monitoring port is used for monitoring transverse unstable combustion in the combustion chamber; the longitudinal high frequency pressure monitoring port can monitor longitudinally unstable combustion in the combustion chamber. According to the invention, the combustion chamber is designed in a rectangular shape, and the injection panel is transversely arranged in a single row, so that self-excitation transverse combustion instability is easily generated, and the mechanism and the control mode of transverse combustion instability in the ignition test process of the engine can be conveniently researched in the follow-up process.
Description
Technical Field
The invention relates to the field of liquid rocket engines, in particular to a rectangular model rocket engine capable of generating self-excitation transverse high-frequency unstable combustion.
Background
The core component of the liquid rocket, namely the liquid rocket engine, is in an extreme environment with high temperature and high pressure in the actual working environment, and particularly, the structural stability and reliability of the engine are seriously tested when unstable combustion occurs. The acoustic coupling of the injector element to the combustion chamber interior can, among other things, seriously affect the combustion state at the time of ignition. When combustion instability occurs, particularly when lateral combustion instability occurs, ablation is caused to a local structure, and therefore, it is extremely important to study the mechanism of generation of combustion instability and the control manner.
At present, the unstable combustion phenomenon of rocket engines is researched in laboratories mainly through a reduced-scale engine test, wherein the reduced-scale engine configuration usually adopts a single nozzle column, and a combustion chamber is designed in a cylindrical configuration. Therefore, the transverse combustion instability is difficult to realize through the single-nozzle cylindrical design.
The model engine with the cylindrical configuration is similar to the actual engine in structure, but is difficult to realize in the aspect of researching combustion instability, particularly transverse combustion instability. The main reasons are: half of the diameter of the model rocket engine with the cylindrical combustion chamber is not suitable to be too large (the too large diameter can cause a complex flow field, the ignition time requirement is longer, and the cooling problem is difficult to solve), while the design of the injection assembly is consistent with that of an actual engine as much as possible, so that a single-nozzle design scheme is often adopted, and the single-nozzle model rocket engine is difficult to realize transverse combustion instability.
Disclosure of Invention
The invention aims to solve the technical problem of the prior art, and provides a rectangular model rocket engine capable of generating self-excited transverse high-frequency unstable combustion, which can research the generation mechanism and control mode of transverse combustion instability in the ignition test process of an engine.
In order to solve the technical problems, the invention adopts the technical scheme that:
a rectangular model rocket engine capable of generating self-excitation transverse high-frequency unstable combustion comprises an oxidant chamber, a jetting panel, a nozzle assembly, a combustion chamber and a tail nozzle.
The oxidant chamber, the injection panel, the combustion chamber and the tail nozzle are coaxially arranged in sequence along the injection direction, and the vertical sections of the oxidant chamber, the injection panel, the combustion chamber and the tail nozzle are rectangular.
The jetting panel is sequentially provided with a fuel cavity and N rows and M columns of fuel jetting hole arrays along the jetting direction; wherein N is more than or equal to 1; m is more than or equal to 3.
The M fuel spray holes in each row of fuel spray hole array are uniformly distributed along the direction parallel to the long edge of the injection panel and are communicated with the fuel cavity.
The nozzle assembly includes a nozzle retaining panel and an equal number of nozzles as fuel orifices.
The nozzle fixing panel is arranged between the oxidant chamber and the fuel chamber in a sealing mode and used for fixing the nozzles, and one nozzle is inserted into each fuel spray hole in a coaxial mode.
Each nozzle is provided with a nozzle oxygen cavity communicated with the oxidant cavity, and an annular fuel injection annular seam is formed between each nozzle and the corresponding fuel spray hole.
The combustion chamber is provided with an ignition interface, a transverse high-frequency pressure monitoring port and a longitudinal high-frequency pressure monitoring port.
The ignition interface is used for installing an ignition device and is used for igniting the propellant in the combustion chamber.
The lateral high frequency pressure monitoring port is used to monitor laterally unstable combustion within the combustion chamber.
The longitudinal high-frequency pressure monitoring port can be matched with the transverse high-frequency pressure monitoring port to monitor the longitudinal unstable combustion in the combustion chamber.
Each nozzle oxygen cavity comprises a cylindrical section and an expansion section which are sequentially distributed along the jetting direction.
And a chamfer is arranged at the upstream of the cylindrical section in each nozzle oxygen cavity.
N=1，M=20。
The tail spray pipe is a contraction pipe, and the contraction ratio is 8.
The combustion chamber is also provided with a combustion low-frequency pressure monitoring port.
The three transverse high-frequency pressure monitoring ports are positioned on the same vertical cross section at the upstream of the combustion chamber.
The fuel chamber is provided with a fuel high frequency pressure monitoring port and a fuel low frequency pressure monitoring port.
The fuel chamber is also provided with a fuel inlet, and the inlet end of the fuel inlet is connected with a fuel supply system.
The oxidant chamber is provided with an oxidant high-frequency pressure monitoring port and an oxidant low-frequency pressure monitoring port.
The invention has the following beneficial effects: according to the invention, the combustion chamber is designed in a rectangular shape, and the injection panel is transversely arranged in a single row, so that self-excitation transverse combustion instability is easily generated, and the mechanism and the control mode of transverse combustion instability in the ignition test process of the engine can be conveniently researched in the follow-up process.
Drawings
FIG. 1 shows a top view of a rectangular model rocket engine capable of producing self-excited transverse high frequency unstable combustion in accordance with the present invention.
FIG. 2 shows an isometric view of a rectangular model rocket engine capable of producing self-excited transverse high frequency unstable combustion in accordance with the present invention.
FIG. 3 shows a cross-sectional view of a rectangular model rocket engine capable of producing self-excited transverse high-frequency unstable combustion in accordance with the present invention.
Figure 4 shows a schematic of the injection configuration of a single nozzle of the present invention.
FIG. 5 is a schematic sectional view showing a single nozzle in the present invention.
Among them are:
10. an oxidant chamber;
11. an oxidant inlet; 12. an oxidant high frequency pressure monitoring port; 13. an oxidant low frequency pressure monitoring port; 14. a seal ring;
20. an injection panel; 21. a fuel injection hole; 22. a fuel chamber; 221. a fuel inlet; 23. a fuel high-frequency pressure monitoring port; 24. a fuel low frequency pressure monitoring port; 25. sealing the channel;
30. a nozzle assembly; 31. a nozzle fixing panel; 32. a nozzle; 33. a nozzle oxygen chamber; 331. chamfering; 332. a cylindrical section; 333. an expansion section; 34. a fuel injection annular seam; 35. an axial spacing ring;
40. a fuel chamber; 41. a transverse high-frequency pressure monitoring port; 42. a longitudinal high-frequency pressure monitoring port; 43. a combustion low frequency pressure monitoring port; 44. an ignition interface;
50. a tail nozzle; 60. and (4) bolts.
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 protection scope of the present invention.
As shown in fig. 1, 2 and 3, a rectangular model rocket engine capable of generating self-excited transverse high frequency unstable combustion includes an oxidizer chamber 10, a jet panel 20, a nozzle assembly 30, a combustion chamber 40 and a jet nozzle 50.
The oxidant chamber, the injection panel, the combustion chamber and the tail nozzle are coaxially arranged in sequence along the injection direction, preferably mounted through bolts 60, and the vertical cross section is rectangular.
The oxidant chamber is provided with an oxidant inlet 11, an oxidant high frequency pressure monitoring port 12 and an oxidant low frequency pressure monitoring port 13.
The inlet end of the oxidant inlet is preferably connected to an oxidant supply system for automatic feeding of the oxidant. Oxygen as the oxidant enters the oxidant chamber through the oxidant supply system, thereby ensuring that the oxygen inlet pressure is uniform for all nozzles.
The high-frequency pressure monitoring port 12 of the oxidant is used for measuring high-frequency pressure pulsation information of an oxidant chamber in the ignition test process of the model rocket engine, and the high-frequency spectrum band is 1 kHz-10 kHz.
The oxidant low-frequency pressure monitoring port 13 is used for measuring low-frequency pressure pulsation information of an oxidant chamber in the ignition test process of the model rocket engine, and the low-frequency spectrum band is within 1 kHz.
The oxidant chamber is preferably sealed by means of a sealing ring 14 and a sealing channel 25 provided on the injection face plate.
The jetting panel is sequentially provided with a fuel cavity 22 and N rows and M columns of fuel jetting hole arrays along the jetting direction; wherein N is more than or equal to 1; m.gtoreq.3, in the present embodiment, N =1 and M =20 are preferred. When N is more than 1, a plurality of rows of transversely arranged rectangular model rocket engines can be researched.
The fuel chamber is preferably provided with a fuel high frequency pressure monitoring port 23, a fuel low frequency pressure monitoring port 24 and a fuel inlet port 221.
The inlet end of the fuel inlet is preferably connected to a fuel supply system for automatic feeding of fuel. In the present embodiment, the fuel is preferably methane or the like. Methane as fuel enters the fuel chamber through the supply line, thereby ensuring a uniform fuel inlet pressure of the injection panel, and the fuel chamber is formed by the cooperation of the nozzle fixing panel and the injection panel as described below.
The fuel high-frequency pressure monitoring port 23 is used for measuring high-frequency pressure pulsation information of a fuel cavity in the ignition test process of the model rocket engine, and the high-frequency spectrum band is 1 kHz-10 kHz.
The fuel low-frequency pressure monitoring port 24 is used for measuring low-frequency pressure pulsation information of a fuel chamber in the ignition test process of the model rocket engine, and the low-frequency spectrum band is within 1 kHz.
The M fuel spray holes 21 in each row of the fuel spray hole array are uniformly distributed along the direction parallel to the long edge of the injection panel and are communicated with the fuel cavity.
The nozzle assembly includes a nozzle fixing plate 31 and nozzles 32 equal in number to the fuel injection holes.
The nozzle fixing panel is arranged between the oxidant chamber and the fuel chamber in a sealing mode and used for fixing the nozzles, and one nozzle is inserted into each fuel spray hole in a coaxial mode.
Each nozzle is preferably a cylindrical coaxial shear nozzle.
As shown in fig. 4 and 5, each nozzle has a nozzle oxygen chamber 33 in communication with the oxidant chamber, and an annular fuel injection annulus 34 is formed between each nozzle and the corresponding fuel nozzle orifice 21.
Each nozzle oxygen chamber comprises a cylindrical section 332 and an expansion section 333 arranged in series along the injection direction.
A cylindrical section 332 and an expanding section 333. Wherein, the expansion section can give certain horizontal initial velocity to the oxygen flow of spouting, is favorable to the mixture with the fuel.
Furthermore, a chamfer 331 is arranged at the upstream of the cylindrical section in each nozzle oxygen cavity, and the arrangement of the chamfers can increase the suction amount of the oxidant.
An axial stop ring 35 is preferably provided on each nozzle of the fuel chamber to limit the axial position of the nozzle. Further, the injection end of the nozzle is retracted inwards and provided with a retracted section.
The combustion chamber is provided with an ignition interface 44, a lateral high-frequency pressure monitoring port 41, a longitudinal high-frequency pressure monitoring port 42, and a combustion low-frequency pressure monitoring port 43.
The ignition interface is used for installing an ignition device and is used for igniting the propellant in the combustion chamber.
The above-mentioned lateral high-frequency pressure monitoring port is used for monitoring the lateral unstable combustion in the combustion chamber. The transverse high-frequency pressure monitoring ports preferably have three, three being located on the same vertical section upstream of the combustion chamber.
The longitudinal high-frequency pressure monitoring ports can be matched with one or more transverse high-frequency pressure monitoring ports to monitor the longitudinal unstable combustion in the combustion chamber.
The combustion low-frequency pressure monitoring port is used for mounting a low-frequency pressure sensor and measuring low-frequency pressure pulsation information of a combustion chamber in the ignition test process of the model rocket engine, and the low-frequency spectrum band is within 1 kHz.
The jet pipe is a contraction pipe, and the contraction ratio is preferably 8.
The mechanism of the invention for generating self-excitation transverse combustion instability is as follows: when the flame propagates under strong lateral disturbance, the flames downstream of the nozzles of the injection panel interact with each other, thereby causing heat release fluctuation and coupling with one of the eigenmodes of the combustion chamber, so as to excite the lateral combustion instability. In order to enhance the mutual influence among the nozzles, the nozzles are closely arranged to form the mutual influence among the nozzles, and simultaneously, the inner section of the combustion chamber is reduced as much as possible while covering the nozzles, so that the influence of the wall surface on the combustion is enhanced. At the same time, the length of the oxidizer nozzle is limited to the length corresponding to the length of the combustion chamber 3/8 wave to the half-wave resonator in order to accommodate the phase of the acoustic modes of the nozzle and the combustion chamber.
The invention takes 20 nozzles as an example, and ignition tests show that: the engine can generate self-excitation transverse high-frequency unstable combustion, and the peak value of the pressure oscillation peak can reach 90% of the average value of the pressure after the measurement of the high-frequency sensor, so that the strong combustion instability phenomenon of the combustion chamber is shown, and the transverse combustion instability generation mechanism and the control mode in the ignition test process of the engine can be conveniently researched subsequently. Wherein the total length of each nozzle is between 3/8 and 1/2 of the combustion chamber pressure chamber wavelength. The method for calculating the wavelength of the combustion chamber pressure chamber is preferably as follows: the sound velocity is estimated based on the temperature in the combustion chamber, and the wavelength of the pressure wave is calculated by combining the pressure oscillation frequency of the combustion chamber measured in a test.
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. A rectangular model rocket engine capable of generating self-excitation transverse high-frequency unstable combustion is characterized in that: the jet nozzle comprises an oxidant chamber, a jet panel, a nozzle assembly, a combustion chamber and a tail nozzle;
the oxidant chamber, the jetting panel, the combustion chamber and the tail nozzle are coaxially arranged in sequence along the jetting direction, and the vertical sections of the oxidant chamber, the jetting panel, the combustion chamber and the tail nozzle are rectangular;
the jetting panel is sequentially provided with a fuel cavity and N rows and M columns of fuel jetting hole arrays along the jetting direction; wherein N is more than or equal to 1; m is more than or equal to 3;
m fuel spray holes in each row of fuel spray hole arrays are uniformly distributed along the direction parallel to the long edge of the injection panel and are communicated with the fuel cavity;
the nozzle assembly comprises a nozzle fixing panel and nozzles with the number equal to that of the fuel spray holes;
the nozzle fixing panel is arranged between the oxidant chamber and the fuel chamber in a sealing mode and used for fixing the nozzles, so that one nozzle is coaxially inserted into each fuel spray hole;
each nozzle is provided with a nozzle oxygen cavity communicated with the oxidant cavity, and an annular fuel injection annular seam is formed between each nozzle and the corresponding fuel spray hole;
the combustion chamber is provided with an ignition interface, a transverse high-frequency pressure monitoring port and a longitudinal high-frequency pressure monitoring port;
the ignition interface is used for installing an ignition device and is used for igniting the propellant in the combustion chamber;
the transverse high-frequency pressure monitoring port is used for monitoring transverse unstable combustion in the combustion chamber;
the longitudinal high-frequency pressure monitoring port can be matched with the transverse high-frequency pressure monitoring port to monitor the longitudinal unstable combustion in the combustion chamber.
2. The rectangular model rocket engine capable of producing self-excited transverse high-frequency unstable combustion according to claim 1, characterized in that: each nozzle oxygen cavity comprises a cylindrical section and an expansion section which are sequentially distributed along the jetting direction.
3. The rectangular model rocket engine capable of producing self-excited transverse high-frequency unstable combustion according to claim 2, characterized in that: the upper reaches of the cylindrical sections in each nozzle oxygen cavity are provided with chamfers.
4. The rectangular model rocket engine capable of producing self-excited transverse high-frequency unstable combustion according to claim 1, characterized in that: n =1, M = 20.
5. The rectangular model rocket engine capable of producing self-excited transverse high-frequency unstable combustion according to claim 1, characterized in that: the tail spray pipe is a contraction pipe, and the contraction ratio is 8.
6. The rectangular model rocket engine capable of producing self-excited transverse high-frequency unstable combustion according to claim 1, characterized in that: the combustion chamber is also provided with a combustion low-frequency pressure monitoring port.
7. The rectangular model rocket engine capable of producing self-excited transverse high-frequency unstable combustion according to claim 1, characterized in that: the three transverse high-frequency pressure monitoring ports are positioned on the same vertical cross section at the upstream of the combustion chamber.
8. The rectangular model rocket engine capable of generating self-excited transverse high-frequency unstable combustion according to claim 1, wherein: the fuel chamber is provided with a fuel high-frequency pressure monitoring port and a fuel low-frequency pressure monitoring port.
9. The rectangular model rocket engine capable of producing self-excited transverse high frequency unstable combustion according to claim 8, wherein: the fuel chamber is also provided with a fuel inlet, the inlet end of which is connected with a fuel supply system.
10. The rectangular model rocket engine capable of producing self-excited transverse high-frequency unstable combustion according to claim 1, characterized in that: the oxidant chamber is provided with an oxidant high-frequency pressure monitoring port and an oxidant low-frequency pressure monitoring port.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210259705.XA CN114645801A (en) | 2022-03-16 | 2022-03-16 | Rectangular model rocket engine capable of generating self-excitation transverse high-frequency unstable combustion |
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| CN202210259705.XA CN114645801A (en) | 2022-03-16 | 2022-03-16 | Rectangular model rocket engine capable of generating self-excitation transverse high-frequency unstable combustion |
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104880320A (en) * | 2015-06-19 | 2015-09-02 | 中国人民解放军装备学院 | Evaluation device and evaluation method for nozzle stability |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104880320A (en) * | 2015-06-19 | 2015-09-02 | 中国人民解放军装备学院 | Evaluation device and evaluation method for nozzle stability |
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