CN110006628B - Underwater propeller jet flow field visualization observation system based on circulating water tunnel - Google Patents
Underwater propeller jet flow field visualization observation system based on circulating water tunnel Download PDFInfo
- Publication number
- CN110006628B CN110006628B CN201910431619.0A CN201910431619A CN110006628B CN 110006628 B CN110006628 B CN 110006628B CN 201910431619 A CN201910431619 A CN 201910431619A CN 110006628 B CN110006628 B CN 110006628B
- Authority
- CN
- China
- Prior art keywords
- flow field
- air cavity
- combustion air
- water tunnel
- pipe
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M10/00—Hydrodynamic testing; Arrangements in or on ship-testing tanks or water tunnels
Abstract
The invention relates to a circulating water tunnel-based visual observation system for a jet flow field of an underwater propeller, and belongs to the technical field of hydraulic and hydroelectric engineering, ocean ships and underwater vehicle engineering. Placing a light source and a high-speed camera at a front glass window, and uniformly distributing a pressure sensor and a temperature sensor on a rear stainless steel plate in a crossed manner; filling water in the water tunnel experiment section, connecting a compressed air pipe, purging the interior of the combustion air cavity, connecting a combustible gas pipe when no liquid water exists in the air cavity, and starting an ignition needle to ignite; and setting the specific positions of another camera and a light source according to the flow field structure in the water tunnel experiment section, and starting the work of experiment observation, data measurement and the like after the ignition is successful. The system of the invention performs experimental research on the influence of gas material properties, gas temperature, gas pressure and water flow velocity on the flow field structure and the flow field characteristic change. The water flow speed can be accurately controlled, and the air and the fuel gas can be quickly switched.
Description
Technical Field
The invention relates to a circulating water tunnel-based visual observation system for a jet flow field of an underwater propeller, and belongs to the technical field of hydraulic and hydroelectric engineering, ocean ships and underwater vehicle engineering.
Background introduction
In the technical field of underwater vehicle engineering, the underwater propulsion technology is the most widely applied missile powered launching technology, and the principle is to obtain reaction thrust by jetting high-speed working media. The small gas engine is the most simple power source for underwater propulsion technology and is the first choice power for various striking type submarine-launched weapons at present. However, when the small-sized gas engine works underwater, the inertia effect of the water environment seriously restricts the normal ejection of gas in the nozzle pipe at the moment of ignition of the engine, so that a large amount of gas is gathered in a combustion chamber, the internal pressure of the engine is overhigh, the working performance is influenced, and even the working fault of the engine is caused, thereby causing the failure of emission. Moreover, a large amount of high-temperature fuel gas is sprayed into water, transient combustion bubbles are formed at the tail of the missile, and complex physical phenomena such as gas-water mixing, heat exchange, phase change and the like exist between the high-temperature combustion bubbles and the water, and the high-temperature combustion bubbles are accompanied with strong hydrodynamic interference; the complex shock wave structure existing in the combustion bubbles and the motion of the shock wave structure can cause the pressure in the airflow field to change dramatically. The comprehensive effects of the violent interaction, the physical change and the shock wave motion among the water and the gas greatly increase the uncertainty of emission, influence the stress of the navigation body and cause the deviation of the motion trail. Therefore, understanding the flow field structure and the flow field characteristic change in the underwater high-speed gas jet process has higher engineering application value on the engine working characteristics such as reasonably estimated thrust value, noise and the like.
At present, the research on underwater gas jet is mainly focused on the change of jet form in a static environment, is mostly carried out based on integral numerical calculation under the condition of a flowing medium, and is rarely related to the research on a flow field structure evolution mechanism formed by high-speed gas jet at different environment medium flow velocities.
Disclosure of Invention
The invention aims to provide a circulating water tunnel-based underwater propeller jet flow field visualization observation system, which is used for experimental research on the influence of gas substance properties, gas temperature, gas pressure and water flow velocity on flow field structure and flow field characteristic changes. The water flow speed can be accurately controlled, and the air and the fuel gas can be quickly switched.
The purpose of the invention is realized by the following technical scheme:
the system comprises a combustor device, a combustion chamber system and a gas injection device;
the burner device comprises a compressed air pipe, a combustible gas pipe, an ignition needle and a fixed base;
the fixed base is of a hollow structure, and the top end of the fixed base is provided with three through holes which are respectively used for connecting a compressed air pipe, a combustible gas pipe and an ignition needle; the air and the combustible gas are mixed at the cavity and then ignited by the ignition needle;
the combustion chamber system comprises a combustion air cavity, high-temperature-resistant glass and a sealing cover plate;
the lower end face of the combustion air cavity is fixed on the upper part of an experimental section of a water tunnel experiment; the fixed base is fixedly arranged at the top end of the combustion air cavity; a flow guide pipe of the gas injection device is fixedly arranged at the bottom end; a visible window is arranged on the side wall of the combustion air cavity; the sealing cover plate seals and fixes the high-temperature resistant glass at the visible window of the combustion air cavity;
the gas injection device comprises a flow guide pipe and a nozzle;
the nozzle is a frustum-shaped circular tube; the nozzle is arranged at the outlet of the flow guide pipe; the spraying direction of the gas is required to be consistent with the water flow direction;
the sealing and fixing mode is that a window fixing channel is arranged around a visual window of the combustion air cavity; the sealing cover plate is welded in the window fixing channel through a welding piece;
the window fixing channel is a hollow cuboid with a rectangular cross section, and the size of the rectangular boundary at the inner side is consistent with that of the rectangular hole at the side surface of the combustion air cavity;
the sealing cover plate is a 'return' type flat plate, the sealing cover plate is divided into an inner part and an outer part, and 30 circular through holes are uniformly formed at the position close to the edge;
the flow guide pipe is an L-shaped round pipe, one side of the flow guide pipe is provided with an internal thread, and the other side of the flow guide pipe is provided with an external thread;
the working process is as follows: the two light sources are respectively arranged at the left and right glass windows of the combustion air cavity, the high-speed camera is arranged at the front glass window, and the pressure sensor and the temperature sensor are uniformly distributed on the rear stainless steel plate in a crossed manner; filling water in the water tunnel experiment section, moving at a preset speed, connecting a compressed air pipe, purging the interior of the combustion air cavity, connecting a combustible gas pipe when no liquid water exists in the air cavity, and starting an ignition needle to ignite; and setting the specific positions of another camera and a light source according to the flow field structure in the water tunnel experiment section, and starting the work of experiment observation, data measurement and the like after the ignition is successful.
Advantageous effects
1. The system for visually observing the jet flow field of the underwater propeller based on the circulating water tunnel can realize measurement of the jet flow field structure of the underwater propeller;
2. the system for visually observing the jet flow field of the underwater propeller based on the circulating water tunnel can flexibly and quickly switch jet gas and realize the observation of the flow field structure in different jet gas states;
3. the system for visually observing the jet flow field of the underwater propeller based on the circulating water tunnel can simultaneously realize the observation of the inner flow field and the gas-liquid two-phase mixing flow field of a combustion chamber under different jet gas parameters (pressure and temperature);
4. the system for visually observing the jet flow field of the underwater propeller based on the circulating water tunnel can realize the observation of a gas-liquid two-phase mixing flow field under different liquid flow rates.
5. The system for visually observing the jet flow field of the underwater propeller based on the circulating water tunnel can flexibly replace different nozzle models, and the experimental device can provide a theoretical basis for the design of the jet structure of the underwater propeller.
Drawings
FIG. 1 is an assembled perspective view of a visual observation system for a jet flow field of an underwater propeller according to the present invention;
FIG. 2 is a partially assembled perspective view of the present invention;
FIG. 3 is a top view of the stationary base of the present invention;
FIG. 4 is a front view of the combustion gas chamber of the present invention;
FIG. 5 is a rear view of the combustion air chamber of the present invention;
FIG. 6 is a top view of the combustion gas chamber of the present invention;
FIG. 7 is an elevation view of a fixed channel of the viewing window of the present invention;
FIG. 8 is a front view of the sealing cover of the present invention;
FIG. 9 is a front view of the draft tube of the present invention;
FIG. 10 is a front view of the nozzle of the present invention.
The device comprises a compressed air pipe 1, a combustible gas pipe 2, an ignition needle 3, a fixed base 4, a combustion air cavity 5, a window fixed channel 6, a sealing cover plate 7, a rectangular sealing ring 8, high-temperature-resistant glass 9, a flow guide pipe 10, a nozzle 11 and a water hole experimental section upper panel 12.
Detailed Description
The following detailed description will specifically describe embodiments of the present invention with reference to the accompanying drawings.
Example 1
A visual observation system of a jet flow field of an underwater propeller based on a circulating water tunnel comprises a burner device, a combustion chamber system and a gas injection device, as shown in figures 1 and 2;
the burner device comprises a compressed air pipe 1, a combustible gas pipe 2, an ignition needle 3 and a fixed base 4, as shown in figure 1;
the fixed base 4 is a convex metal block, and the center of the upper end surface is provided with three threaded holes which are respectively used for connecting a compressed air pipe, a combustible gas pipe and an ignition needle; the edges of the periphery of the lower end face are uniformly provided with 12 circular through holes as shown in figure 3;
the combustion chamber system comprises a combustion air chamber 5, a window fixing channel 6, a sealing cover plate 7, a rectangular sealing ring 8 and high-temperature-resistant glass 9, as shown in figures 1 and 2;
the combustion air cavity 5 is a square cavity, a square hole is formed in the center of the upper end face, 12 circular through holes are formed around the square hole, and the size and the position of each circular through hole are consistent with those of the 12 circular through holes of the fixed base, as shown in fig. 4 and 6; a threaded through hole is formed in the center of the lower end face, and 4 circular through holes are formed in the edge of the lower end face, as shown in fig. 6; three side surfaces are respectively provided with a rectangular hole, and the center of the other side surface is uniformly provided with 9 threaded holes for mounting a pressure sensor and a temperature sensor, as shown in fig. 4 and 5;
the window fixing channel 6 is a hollow cuboid with a rectangular cross section, and the size of the rectangular boundary at the inner side is consistent with that of the rectangular hole at the side surface of the combustion air cavity, as shown in fig. 7;
the sealing cover plate 7 is a 'return' type flat plate, the sealing cover plate is divided into an inner part and an outer part, and 30 circular through holes are uniformly formed at the edge, as shown in fig. 2 and 8;
the gas injection device comprises a guide pipe 10 and a nozzle 11;
the flow guide pipe 10 is an L-shaped round pipe, one side of which is provided with an internal thread and the other side of which is provided with an external thread, as shown in figure 9;
the nozzle 11 is a frustum-shaped circular tube, and an external thread is formed on one side of the frustum-shaped circular tube, as shown in fig. 10;
the connection mode is as follows: the window fixed channel 6 is respectively fixed at the positions of rectangular holes on three side surfaces of the combustion air cavity 5 in a welding mode; the lower end face of the combustion air cavity 5 is fixed on an upper panel of the water tunnel experiment section through a bolt and a nut, the bolt is selected according to the diameter of a circular through hole at the edge of the lower end face of the combustion air cavity according to GB/T5782 and 2000-plus material, and the nut is selected according to the bolt; the lower end face of the fixed base 4 is fixed on the upper end face of the combustion air cavity 5 through bolts and nuts, the bolts refer to GB/T5782 and 2000, the bolts are selected according to the diameters of 12 circular through holes in the upper end face of the combustion air cavity and the lower section of the fixed base, and the nuts are selected according to the bolts; the compressed air pipe 1, the combustible gas pipe 2 and the ignition needle 3 are fixed on the upper end surface of the fixed base 4 through threads; the inner sealing cover plate 7 is fixed on the window fixing channel 6 in a welding mode; the high-temperature-resistant glass 9, the rectangular sealing ring 8 and the outer sealing cover plate 7 are fixed on the window fixing channel 6 through bolts and nuts, in order to prevent gas leakage in the combustion gas cavity 5, the rectangular sealing ring 8 is added between the high-temperature-resistant glass 9 and the inner and outer sealing cover plates 7 at the same time, the bolts refer to GB/T5782 and the other 2000 materials, the bolts are selected according to the diameter of a circular through hole in the sealing cover plate, and the nuts are selected according to the bolts; one end of the external thread of the draft tube 10 is connected with the upper panel 12 of the water tunnel experiment section and the lower end face of the combustion air cavity 5 through threads, and the other end is connected with the nozzle 11 through threads.
The working process is as follows: the two light sources are respectively arranged at the left and right glass windows of the combustion air cavity 5, the high-speed camera is arranged at the front glass window, and the pressure sensor and the temperature sensor are crossly and uniformly distributed on the rear stainless steel plate; filling water in the water tunnel experimental section, moving at a preset speed, connecting the compressed air pipe 1, purging the interior of the combustion air cavity 5, connecting the combustible gas pipe 2 when no liquid water exists in the combustion air cavity 5, and starting the ignition needle 3 to ignite; and setting the specific positions of another camera and a light source according to the flow field structure in the water tunnel experiment section, and starting the work of experiment observation, data measurement and the like after the ignition is successful.
Finally, it should be noted that the above is only for illustrating the technical solutions of the present invention, and those skilled in the art can modify the technical solutions of the present invention or substitute them with equivalent ones. All changes, equivalents, modifications and the like which come within the spirit and principle of the invention are desired to be protected.
Claims (7)
1. Visual observation system in underwater propulsor efflux flow field based on circulation water tunnel, its characterized in that: comprises a burner device, a combustion chamber system and a gas injection device;
the burner device comprises a compressed air pipe, a combustible gas pipe, an ignition needle and a fixed base;
the fixed base is of a hollow structure, and the top end of the fixed base is provided with three through holes which are respectively used for connecting a compressed air pipe, a combustible gas pipe and an ignition needle; the air and the combustible gas are mixed at the cavity and then ignited by the ignition needle;
the combustion chamber system comprises a combustion air cavity, high-temperature-resistant glass and a sealing cover plate;
the lower end face of the combustion air cavity is fixed on the upper part of an experimental section of a water tunnel experiment; the fixed base is fixedly arranged at the top end of the combustion air cavity; a flow guide pipe of the gas injection device is fixedly arranged at the bottom end; a visible window is arranged on the side wall of the combustion air cavity; the sealing cover plate seals and fixes the high-temperature resistant glass at the visible window of the combustion air cavity;
the gas injection device comprises a flow guide pipe and a nozzle.
2. The circulating water tunnel-based underwater propeller jet flow field visualization observation system of claim 1, wherein: the nozzle is a frustum-shaped circular tube; the nozzle is arranged at the outlet of the flow guide pipe; the gas spraying direction is consistent with the water flow direction.
3. The circulating water tunnel-based underwater propeller jet flow field visualization observation system of claim 1, wherein: the sealing and fixing mode is that a window fixing channel is arranged around a visual window of the combustion air cavity; the sealing cover plate is welded in the window fixing channel through a welding piece.
4. The circulating water tunnel-based underwater propeller jet flow field visualization observation system of claim 3, wherein: the window fixing channel is a hollow cuboid with a rectangular cross section, and the size of the rectangular boundary at the inner side is consistent with that of the rectangular hole at the side surface of the combustion air cavity.
5. The circulating water tunnel-based underwater propeller jet flow field visualization observation system of claim 1, wherein: the sealing cover plate is a 'return' type flat plate, the sealing cover plate is divided into an inner part and an outer part, and through holes are uniformly formed at the edge of the sealing cover plate.
6. The circulating water tunnel-based underwater propeller jet flow field visualization observation system of claim 1, wherein: the flow guide pipe is an L-shaped round pipe, one side of the flow guide pipe is provided with an internal thread, and the other side of the flow guide pipe is provided with an external thread.
7. Method for performing a propeller jet flow field using a sight system according to any of claims 1 to 6, characterised in that: the two light sources are respectively arranged at the left and right glass windows of the combustion air cavity, the high-speed camera is arranged at the front glass window, and the pressure sensor and the temperature sensor are uniformly distributed on the rear stainless steel plate in a crossed manner; filling water in the water tunnel experiment section, moving at a preset speed, connecting a compressed air pipe, purging the inside of a combustion air cavity, connecting a combustible gas pipe when no liquid water exists in the combustion air cavity, and starting an ignition needle to ignite; the specific positions of another camera and a light source are arranged according to the flow field structure in the water tunnel experiment section, and the experiment observation and data measurement work can be started after the ignition is successful.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910431619.0A CN110006628B (en) | 2019-05-22 | 2019-05-22 | Underwater propeller jet flow field visualization observation system based on circulating water tunnel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910431619.0A CN110006628B (en) | 2019-05-22 | 2019-05-22 | Underwater propeller jet flow field visualization observation system based on circulating water tunnel |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110006628A CN110006628A (en) | 2019-07-12 |
| CN110006628B true CN110006628B (en) | 2020-02-14 |
Family
ID=67177709
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910431619.0A Active CN110006628B (en) | 2019-05-22 | 2019-05-22 | Underwater propeller jet flow field visualization observation system based on circulating water tunnel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110006628B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110567678B (en) * | 2019-08-30 | 2021-06-15 | 中国船舶工业集团公司第七0八研究所 | Beam device for testing hydrodynamic performance of propeller |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101464206B (en) * | 2009-01-20 | 2010-08-11 | 西安交通大学 | Test device for turbulent flow gas-liquid blending flow field in transverse flow |
| JP2018507138A (en) * | 2015-03-03 | 2018-03-15 | マサチューセッツ インスティテュート オブ テクノロジー | Underwater vehicle design and control method |
| CN104807612B (en) * | 2015-05-05 | 2017-03-29 | 北京理工大学 | The many field synchronization measuring systems of unsteady cavitating flows based on circulating water tunnel |
| KR102065824B1 (en) * | 2017-08-31 | 2020-01-13 | 한국해양과학기술원 | A rectangular prism installing method on the large cavitation tunnel |
| CN109297678A (en) * | 2018-11-06 | 2019-02-01 | 北京理工大学 | A kind of cavitation gas-liquid flow field measuring system based on conducting probe |
-
2019
- 2019-05-22 CN CN201910431619.0A patent/CN110006628B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN110006628A (en) | 2019-07-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110006628B (en) | Underwater propeller jet flow field visualization observation system based on circulating water tunnel | |
| TW360607B (en) | Underwater two-phrase ramjet engine | |
| CN111122767A (en) | Detachable solid rocket engine jet pipe throat lining ablation test device | |
| CN109882601B (en) | Air gun head for underwater high-pressure air ice breaking experiment | |
| CN108035824A (en) | A kind of pulsed secondary jet thrust vector control system | |
| CN108612598B (en) | Method for changing combustion mode of bi-mode ramjet engine and engine combustion chamber | |
| CN109505711B (en) | Gas-gas small rocket device for generating high-temperature supersonic gas | |
| CN100425819C (en) | Steam booster of rocket propeller | |
| CN110425057B (en) | Gas flow guiding device for vehicle-mounted rocket launching | |
| GB749560A (en) | Device for controlling the flow of a fluid by means of an auxiliary flow | |
| CN109736965B (en) | Pulse injection device, liquid fuel supply system and scramjet engine | |
| CN202073656U (en) | Underwater gas-liquid two-phase engine | |
| CN102251880A (en) | Underwater gas-liquid two-phase engine | |
| CN116558767A (en) | Small supersonic shock tunnel test section with easily-assembled and disassembled components | |
| CN110160744B (en) | Immersed gas-liquid two-phase jet flow unstable flow field measuring system | |
| CN111023150B (en) | Extension plate for combustion chamber | |
| CN108760324A (en) | A kind of wave absorber of solid propellant rocket underwater test | |
| ZHANG et al. | Numerical analysis of influence of charge parameters on flow field around sealed muzzle of underwater machine gun | |
| CN114607526A (en) | Impact type model engine for researching tangential unstable combustion of double-liquid-phase propellant | |
| CN110454299B (en) | Pulse detonation engine based on Stirling cycle cooling | |
| KR102065824B1 (en) | A rectangular prism installing method on the large cavitation tunnel | |
| CN114753943B (en) | Single-sided pressure-bearing double-pulse isolation device of double-pulse engine | |
| EP1568603B1 (en) | Marine propulsion system and marine vessel having same | |
| CN116080881A (en) | Two-phase stamping underwater propulsion system containing non-condensable gas | |
| CN113049256A (en) | High-temperature and high-speed flame flow generating device for simulating service environment of aircraft engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |