CN110185555B - Cold flow experimental system of stamping engine with embedded rocket - Google Patents
Cold flow experimental system of stamping engine with embedded rocket Download PDFInfo
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- CN110185555B CN110185555B CN201910412063.0A CN201910412063A CN110185555B CN 110185555 B CN110185555 B CN 110185555B CN 201910412063 A CN201910412063 A CN 201910412063A CN 110185555 B CN110185555 B CN 110185555B
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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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- Combustion & Propulsion (AREA)
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- Testing Of Engines (AREA)
Abstract
The invention relates to a cold flow experimental device for an embedded rocket ramjet, and belongs to the field of sound field testing of the embedded rocket ramjet. The experimental system mainly comprises an air supply part, an air path part, a data acquisition part and a working part. The working part, namely the scaling prototype is the most important device of the whole experiment system and comprises the following components: the device comprises a pressing plate, a metal plate, a cover plate, a bottom plate, a glass plate, an embedded rocket flat gasket, an embedded plate flat gasket, a bottom plate flat gasket, a hexagon bolt and a nut. The invention simulates the influence of different conditions on the flow field of the main combustion chamber by changing the airflow pressure introduced into the interior of the embedded rocket, the expansion ratio of the embedded rocket and the shape of the outlet of the embedded rocket. The device makes up the vacancy of the cold flow compression ratio experiment testing device of the embedded rocket ramjet. The device performs two-dimensional simplified scaling on a full-size engine model, so that the purposes of simplicity, convenience and easiness in testing are achieved, and certain forerunner guidance is provided for full-size engine exploration.
Description
Technical Field
The invention relates to a cold flow experimental device for an embedded rocket ramjet, and belongs to the field of sound field testing of the embedded rocket ramjet.
Background
The ramjet has the advantages of higher specific impact and higher thrust-weight ratio. However, the ramjet engine is susceptible to the working environment and is prone to stall when flying at high altitude. In order to make up for the defect of the ramjet, the embedded rocket engine is introduced as a supplementary heat source, so that the ramjet has the advantages of high specific thrust and high thrust-weight ratio and the rocket engine is not influenced by the working environment. The embedded rocket ramjet is taken as a novel combined engine, and has the advantages of both the rocket engine and the ramjet, but because the embedded rocket is introduced, two air flow mixing paths are formed in a combustion chamber, the air flow mixing flow field of the combined engine is complex, unstable combustion in the engine is easily formed, and the pressure in the engine is unstable. The research on the embedded rocket ramjet has the prior art that the simulation analysis is focused, the simulation analysis spans to the actual application, and an experimental part is lacked, so unsafe phenomena are easy to occur in the actual application process, and resource waste is caused.
The cold flow experiment is mainly developed at normal temperature, the research object is mainly flow field distribution, and the cold flow experiment can provide theoretical basis for the subsequent heat flow experiment. Meanwhile, the cold flow experiment is quick and convenient, is not influenced by environmental factors, and can effectively help to complete development and authentication experiments in actual research and development, so that the research and development period is shortened, and the cold flow experiment has wide application in the research of various spray pipes, engines and even exhaust system fields.
Disclosure of Invention
The invention aims to provide a cold flow experimental device of an embedded rocket ramjet, which is beneficial to developing experimental research of the embedded rocket ramjet, provides experimental data tests except theoretical simulation for the sound field characteristics of a combustion chamber of the embedded rocket ramjet, and makes up the vacancy of the experimental test device of the engine. The device performs two-dimensional simplified scaling on a full-size engine model, so that the purposes of simplicity, convenience and easiness in testing are achieved, and certain forerunner guidance is provided for full-size engine exploration.
The purpose of the invention is realized by the following technical scheme.
The invention discloses a cold flow experiment system of an embedded rocket ramjet, which mainly comprises an air supply and gas path system, a data acquisition system and a scaling prototype experiment device.
The air supply and air path system mainly comprises an air supply part and an air path part. The air supply part consists of a high-pressure air bottle, is used as an air source of the whole experiment system and provides initial condition parameters for the cold flow experiment testing device; the gas circuit part consists of a high-pressure pipeline and an electromagnetic valve, and the electromagnetic valve is positioned between the gas supply part and the scaling model machine experiment device and is used for controlling the supply of gas flow entering the experiment device;
the data acquisition system comprises pressure data acquisition and flow field visualization equipment. The pressure data acquisition comprises a pressure sensor and a multifunctional dynamic signal acquisition instrument, and is mainly used for acquiring real-time pressure of a required position. The flow field visualization equipment comprises a schlieren instrument and a high-speed camera and is used for observing airflow;
the scaling prototype experimental device mainly comprises a cover plate, a bottom plate and an embedded rocket. The embedded rocket is arranged at the corresponding position of the bottom plate, and the cover plate and the bottom plate are pressed and sealed mutually to simulate the embedded rocket ramjet.
The cover plate is provided with a first through groove in the center part, and an embedded metal plate or an embedded transparent plate can be embedded in the first through groove. The embedded metal plate is made of the same material as the whole experimental device and is provided with a pressure measuring hole, so that pressure data can be acquired; the embedded transparent plate is made of transparent materials, so that the embedded transparent plate is convenient to see and can visually observe the airflow change in the combustion chamber.
The bottom plate is provided with a groove, and the shape of the groove is consistent with the outline of the ramjet. A second through groove is formed in the groove; the second through groove corresponds to the first through groove in position, an embedded transparent plate can be installed, and the second through groove and the embedded transparent plate at the first through groove act together, so that the combustion chamber can be observed visually; an embedded rocket slot is required to be formed in the groove, the shape of the embedded rocket slot is the same as the shape of the outline of the embedded rocket, and the forming position is located at the corresponding position of the embedded rocket in the embedded rocket ramjet, so that the embedded rocket is convenient to fix; and the embedded rocket slot is provided with an air vent for air intake of the embedded rocket.
The influence of different jet conditions on the flow field of the main combustion chamber can be simulated by changing the pressure of the airflow introduced into the interior of the embedded rocket and changing the size of the throat part of the nozzle of the embedded rocket.
The working process is as follows: the system is placed in a simulated high-altitude environment; an air inlet port simulated by the bottom plate and the cover plate is used for ventilating the device, and the airflow is controlled to simulate a high-Mach number environment; high-pressure airflow is introduced into the embedded rocket through the vent holes to form high-speed jet flow, the high-speed jet flow enters the combustion chamber, the two airflows are mixed, and the experimental device simulates the working condition of the ramjet engine after air inlet.
Has the advantages that:
1. the cold flow experiment system for the embedded rocket ramjet disclosed by the invention makes up the vacancy of the cold flow compression ratio experiment testing device for the embedded rocket ramjet, reduces the loss in practical application and improves the success rate. The device performs two-dimensional simplified scaling on a full-size engine model, so that the purposes of simplicity, convenience and easiness in testing are achieved, and certain forerunner guidance is provided for full-size engine exploration.
2. The invention discloses a cold flow experimental system of an embedded rocket ramjet. The air flow switch entering the combustion chamber of the embedded rocket can be controlled by the electromagnetic valve on the air path. The pressure inside the combustion chamber of the embedded rocket can be quickly reached to the required pressure.
3. The invention discloses a cold flow experimental system of an embedded rocket ramjet. The influence of different jet conditions on the flow field of the main combustion chamber is simulated by changing the pressure of the airflow introduced into the interior of the embedded rocket and changing the size of the throat part of the nozzle of the embedded rocket.
Drawings
FIG. 1 is an overall view of a cold flow experimental system of a scale model machine of an embedded rocket ramjet; FIG. 1(a) is a frame diagram of an experimental system of a scaling prototype; FIG. 1(b) is a schematic diagram of parts of an experimental system of a scaling prototype;
FIG. 2 is a cold flow experiment airflow flow diagram of a scale model machine of an embedded rocket ramjet engine;
FIG. 3 is a schematic diagram of a cold flow experiment scaling prototype of an embedded rocket ramjet; FIG. 3(a) is a front view of a scaling prototype; FIG. 3(b) is a side view of a scale prototype; FIG. 3(c) is a top view of the scaling prototype;
FIG. 4 is a schematic diagram of a three-dimensional structure of a cold flow experiment scaling prototype of an embedded rocket ramjet.
The device comprises a pressing plate 1, a metal plate 2, a cover plate 3, a bottom plate 4, a glass plate 5, an embedded rocket 6, an embedded hexagonal screw 7-M5, a pin 8, an embedded hexagonal screw 9-M6, an embedded rocket flat gasket 10, an embedded plate flat gasket 11, a bottom plate flat gasket 12, an air source interface 13, a pressure measuring hole 14, a hexagon bolt 15-M12 and a hexagon nut 16-M12.
Detailed Description
For a better understanding of the objects and advantages of the present invention, reference should be made to the following detailed description taken in conjunction with the accompanying drawings and examples.
Example 1:
a cold flow experiment system of an embedded rocket ramjet mainly comprises an air supply and gas path system, a data acquisition system and a scaling prototype experiment device.
The data acquisition system mainly comprises a pressure data acquisition and visualization device. The pressure sensor is mainly arranged with: 5 sensors are uniformly distributed along the central axis of the combustion chamber from the head to the tail of the combustion chamber; 2 sensors are distributed at the position of the head of the combustion chamber, which is close to the wall surface, and the radial position of the sensors is consistent with the position of the 2 sensors of the central axis, which is close to the head of the combustion chamber; and the gas collection position of the embedded rocket is used for monitoring whether the airflow of the embedded rocket reaches the required pressure.
The scaling prototype experiment system comprises: the pressure plate comprises a pressure plate 1, a metal plate 2, a cover plate 3, a bottom plate 4, an embedded transparent plate 5, an embedded rocket 6, an M5 hexagon socket head cap screw 7, a pin 8, an M6 hexagon socket head cap screw 9, an embedded rocket flat gasket 10, an embedded plate flat gasket 11, a bottom plate flat gasket 12, an air source interface 13, a pressure measuring hole 14, an M12 hexagon bolt 15 and an M12 hexagon nut 16.
The cold flow experiment scaling prototype of the embedded rocket ramjet is of a cuboid structure. The embedded rocket 6 is positioned on the bottom plate 4 through two pins 8 and is fixed on the bottom plate 4 through four M5 hexagon socket head cap screws 7, and meanwhile, an embedded rocket flat gasket 10 made of rubber is clamped between the embedded rocket 6 and the bottom plate 4 to play a sealing role; the cover plate 3 and the bottom plate 4 are connected through eight matched M12 hexagon bolts 15 and M12 hexagon nuts 16, and a bottom plate flat gasket 12 made of rubber is clamped between the cover plate 3 and the bottom plate 4 to play a role of sealing. A square hole is formed in the cover plate 3 and used for placing the metal plate 2, an embedded plate flat gasket 11 made of rubber is clamped between the metal plate 2 and the cover plate 3, and the embedded plate flat gasket is fixed on the cover plate 3 through the pressure plate 1 and eight M6 hexagon screws 9. A square hole is arranged on the bottom plate for placing the embedded transparent plate 5, and the overpressure plate 1 and eight M6 hexagon screws 9 are fixed on the bottom plate 4. The air source interface 13 is connected with the air circuit part. The pressure measuring hole 14 is connected with the pressure sensor and is connected with a pressure data acquisition device for measuring the pressure in the main combustion chamber. A schlieren instrument and a high-speed camera are arranged outside the embedded transparent plate and used for observing and recording the change of the flow field in the main combustion chamber.
In the experimental process, the influence of different jet conditions on the flow field of the main combustion chamber can be simulated by changing the pressure of the airflow introduced into the interior of the embedded rocket and changing the size of the throat of the nozzle of the embedded rocket.
The whole experimental method comprises the following steps:
a. placing the experimental system in a simulated high-altitude environment; an air inlet port simulated by the bottom plate and the cover plate is used for ventilating the device, and the airflow is controlled to simulate a high-Mach-number environment.
b. Assembling an experiment system according to an experiment system diagram, and fixing a cold flow experiment device on a support to keep the cold flow experiment device stable; the embedded glass plate, the schlieren instrument and the high-speed camera center are kept in a straight line. And the sensors are arranged on the measuring points and used for measuring the pressure change of the flow field.
c. Opening a data acquisition system, and setting acquisition parameters according to different sensors; opening the high-speed camera to ensure that the high-speed camera can shoot the condition of the flow field in the cold flow tester;
d. and closing the electromagnetic valve, opening a high-pressure gas cylinder of the gas supply system, and adjusting the outlet pressure of the pressure reducing valve to ensure that the pressure of the gas flow before entering the cold flow tester reaches a certain pressure value, so that when the electromagnetic valve is opened, the interior of the embedded rocket instantaneously reaches the pressure of the experimental design.
e. And opening a data acquisition button of the data acquisition system, opening the high-speed camera and starting shooting. Then the electromagnetic valve is opened, and high-pressure airflow is introduced into the small internally-embedded rocket. And collecting the pressure change and flow field change conditions in the cold flow tester. After a period of time, the solenoid valve is closed, the ventilation is stopped, and then the data acquisition system and the high speed camera are stopped.
f. And (d) repeating the steps c and d, developing experimental research of different chamber pressures of the embedded small rocket, and recording related pressure data and flow field change conditions.
g. And after the experiment is finished, closing the data acquisition system, the high-speed camera, the electromagnetic valve and the gas cylinder pressure reducing valve.
The embodiment has better effect.
The above detailed description is intended to illustrate the objects, aspects and advantages of the present invention, and it should be understood that the above detailed description is only exemplary of the present invention and is not intended to limit the scope of the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (1)
1. Embedded rocket ramjet cold flow experimental system, its characterized in that: the experimental system mainly comprises a gas supply and gas path system, a data acquisition system and a scaling prototype experimental device;
the air supply and air path system mainly comprises an air supply part and an air path part; the air supply part consists of a high-pressure air bottle, is used as an air source of the whole experiment system and provides initial condition parameters for the cold flow experiment testing device; the gas circuit part consists of a high-pressure pipeline and an electromagnetic valve, and the electromagnetic valve is positioned between the gas supply part and the scaling prototype experimental device and is used for controlling the supply of gas flow entering the scaling prototype experimental device;
the data acquisition system comprises pressure data acquisition and flow field visualization equipment; the pressure data acquisition comprises a pressure sensor and a multifunctional dynamic signal acquisition instrument, and is mainly used for acquiring real-time pressure of a required position; the flow field visualization equipment comprises a schlieren instrument and a high-speed camera and is used for observing airflow;
the scaling prototype experimental device comprises a cover plate, a bottom plate and an embedded rocket; the embedded rocket is arranged at the corresponding position of the bottom plate, and the embedded rocket ramjet is simulated by utilizing the pressing and sealing of the cover plate and the bottom plate;
the central part of the cover plate is provided with a first through groove, and an embedded metal plate is embedded in the first through groove; the embedded metal plate is provided with a pressure measuring hole for pressure data acquisition;
the bottom plate is provided with a groove, and the shape of the groove is consistent with the outline of the ramjet; a second through groove is formed in the groove; the second through groove corresponds to the first through groove in position, and an embedded transparent plate is installed, so that visual observation of the scaling model machine experiment device is facilitated; an embedded rocket slot is formed in the groove, the shape of the embedded rocket slot is the same as the shape of the outline of the embedded rocket, and the forming position of the embedded rocket slot is located at the corresponding position of the embedded rocket in the embedded rocket ramjet, so that the embedded rocket is convenient to fix; and the embedded rocket slot is provided with an air vent for air intake of the embedded rocket.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910412063.0A CN110185555B (en) | 2019-05-17 | 2019-05-17 | Cold flow experimental system of stamping engine with embedded rocket |
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| CN201910412063.0A CN110185555B (en) | 2019-05-17 | 2019-05-17 | Cold flow experimental system of stamping engine with embedded rocket |
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| CN110185555A CN110185555A (en) | 2019-08-30 |
| CN110185555B true CN110185555B (en) | 2020-08-18 |
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| CN113202655B (en) * | 2021-06-07 | 2022-05-24 | 北京理工大学 | Solid-liquid stamping combined engine |
| CN114352440A (en) * | 2022-01-07 | 2022-04-15 | 北京理工大学 | Modular solid rocket ramjet ground direct connection test device |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| DE3608582A1 (en) * | 1986-03-14 | 1987-09-17 | Gerhard Nerenberg | Device for driving an aircraft |
| FR2975468B1 (en) * | 2011-05-16 | 2016-01-01 | Mbda France | CONTINUOUS DETONATING WAVE MOTOR AND FLYWHEEL EQUIPPED WITH SUCH A MOTOR |
| CN102400814B (en) * | 2011-10-27 | 2013-09-18 | 北京航空航天大学 | Solid-liquid hybrid rocket ramjet for test |
| JP2015099044A (en) * | 2013-11-18 | 2015-05-28 | 株式会社Ｉｈｉエアロスペース | Cooling chamber |
| CN105651809A (en) * | 2015-12-31 | 2016-06-08 | 中国人民解放军国防科学技术大学 | Experimental device for particle combustion under high speed air flow |
| CN109339983A (en) * | 2018-11-22 | 2019-02-15 | 内蒙航天动力机械测试所 | The verifying device of the virtual high mould experimental enviroment model of solid propellant rocket |
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