CN109238648A - Propulsive thrust PIV tests high pressure trace particle delivery device - Google Patents
Propulsive thrust PIV tests high pressure trace particle delivery device Download PDFInfo
- Publication number
- CN109238648A CN109238648A CN201811264867.2A CN201811264867A CN109238648A CN 109238648 A CN109238648 A CN 109238648A CN 201811264867 A CN201811264867 A CN 201811264867A CN 109238648 A CN109238648 A CN 109238648A
- Authority
- CN
- China
- Prior art keywords
- high pressure
- pressure
- trace
- propulsive thrust
- sieve pore
- 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.)
- Pending
Links
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 present invention provides a kind of propulsive thrust PIV test high pressure trace particle delivery device, including high pressure trace displaying particle generator pressure duct, it and further include high pressure nozzle and pressure stabilizing sieve pore device, high pressure trace displaying particle generator is connect with high pressure nozzle, high pressure nozzle is connect by pressure duct with pressure stabilizing sieve pore device, and pressure stabilizing sieve pore device sprays the high pressure gas with trace particle.The trace particle that the present apparatus sprays has the characteristics that be of moderate size, uniformity is good, followability is excellent, can really reflect the flow field characteristic of nacelle outlet, and the problem that sucks again for research propulsive thrust nacelle provides reliable guarantee.Present invention can also apply in such as thrust vectoring, intake and exhaust dynamic simulation trial, application prospect is very wide, problem is sucked again with very important realistic meaning for research propulsive thrust nacelle.
Description
Technical field
The present invention relates to a kind of propulsive thrust PIV to test high pressure trace particle delivery device.
Background technique
Engine reverse thrust technology extensive application in current aeronautical technology, thrust reverser, which is one, can make original
Jet-stream wind transfers the device for spraying air-flow forward backward for this.When device starting, engine can change air-flow flow pass, produce
A raw reversed thrust.Aircraft landing is sliding run and take off interrupt sliding run during to reduce its ground run distance, to reduce to race
The limitation of road length, aircraft is frequently with engine reverse thrust technology.Propulsive thrust technology is to civil aviation construction also economy with higher
Value and practical value, runway required for the application of thrust reverser makes aircraft landing is sliding to run greatly are shortened, are landed
Safety greatly improves, the considerable economic benefit created for civil aviation construction.
Thrust reverser unlatching can be such that aircraft running speed quickly reduces, and run in the sliding of initial stage aircraft of this process
Speed is higher, is easy to be stopped by the incoming flow of high speed by the air-flow that THR REV sprays forward, turns back and flow backward, it is not easy to send out
Life sucks problem again；However after running speed is lower than a certain speed, the reverse thrusting airflow being discharged from THR REV will be started
Machine sucks again.(actual engine is under the medium above power before and after fan by the compression of fan for reverse thrusting airflow
The temperature difference will be up to 30~60 DEG C), temperature is higher than incoming flow, when the air-flow that this is higher than environment temperature is sucked by engine again, just
Occur sucking phenomenon again, the air-flow sucked again by engine will lead to lip charge air flow temperature distributing disproportionation before fan, produce
Raw Temperature Distribution distortion, the distortion can induce air-flow to the non-uniform shock of engine blower blade, destroy when fan rotates
Dynamic balancing causes the flutter of fan blade, reduces the safety of engine, influences normal service life.
Situation is sucked again at different wind speeds to obtain propulsive thrust nacelle, needs to carry out propulsive thrust nacelle PIV flow field survey
Test.A kind of high pressure trace particle delivery device applied to propulsive thrust PIV test is needed, is to carry out propulsive thrust PIV test
Key equipment.
Summary of the invention
Based on the above shortcomings, the object of the present invention is to provide a kind of propulsive thrust PIV test high pressure trace particles to launch
Device can launch uniform trace particle in pressure duct front end, make to pass through in the case where not destroying nacelle exit flow field
PIV test sucks situation again studying propulsive thrust nacelle and is possibly realized.
The technical solution of the invention is as follows: a kind of propulsive thrust PIV test high pressure trace particle delivery device, including high pressure
Trace displaying particle generator pressure duct, and further include high pressure nozzle and pressure stabilizing sieve pore device, high pressure trace displaying particle generator with
High pressure nozzle connection, high pressure nozzle are connect by pressure duct with pressure stabilizing sieve pore device, and pressure stabilizing sieve pore device sprays band tracer grain
The high pressure gas of son.
The present invention also has following technical characteristic: the pressure stabilizing sieve pore device includes shell and sieve nest, and sieve nest is mounted on
In shell, the space between sieve nest and shell is pressure stabilizing cavity, is provided with multiple sieve pores on sieve nest.
Beneficial effects of the present invention and advantage are as follows: the present apparatus spray trace particle have be of moderate size, uniformity is good,
The features such as followability is excellent can really reflect the flow field characteristic of nacelle outlet, suck problem again for research propulsive thrust nacelle
Reliable guarantee is provided.Present invention can also apply in such as thrust vectoring, intake and exhaust dynamic simulation trial, application prospect is very
It is wide, problem is sucked again with very important realistic meaning for research propulsive thrust nacelle.
Detailed description of the invention
Fig. 1 is the schematic illustration of the present apparatus；
Fig. 2 is pressure stabilizing sieve pore principle of device schematic diagram；
Wherein 1, liquid trace particle, 2, high pressure trace displaying particle generator, 3, high pressure nozzle, 4, mixing chamber, 5, high-voltage tube
Road, 6, pressure stabilizing sieve pore device, 7, pressure stabilizing cavity, 8, sieve pore device.
Specific embodiment
Following specific implementation examples are enumerated in conjunction with Figure of description, technical scheme is described further.
Embodiment 1
As shown in Figure 1, a kind of propulsive thrust PIV tests high pressure trace particle delivery device, including high pressure trace particle occurs
Device pressure duct, the present apparatus further include high pressure nozzle and pressure stabilizing sieve pore device, and high pressure trace displaying particle generator and high pressure nozzle connect
It connects, high pressure nozzle is connect by pressure duct with pressure stabilizing sieve pore device, and trace displaying particle generator drives high-pressure plunger using motor
By liquefied trace particle boost in pressure to operating pressure (5-7MPa) after pump, then trace particle after pressurization is injected by nozzle
It inside pressure duct and is atomized, is uniformly mixed air-flow with atomization trace particle and passes through
Nozzle sprays, and the high pressure gas comprising trace particle of ejection can carry out PIV test.
As shown in Fig. 2, pressure stabilizing sieve pore device includes shell and sieve nest, sieve nest is mounted in shell, between sieve nest and shell
Space be pressure stabilizing cavity, be provided with multiple sieve pores on sieve nest.Its act on be make high pressure draught first inside the pressure stabilizing cavity of the device into
It is uniformly sprayed after row mixing using sieve pore, spraying the high pressure gas with trace particle can be carried out the test of PIV flow field survey.
The propulsive thrust PIV test high pressure trace particle delivery device of the present embodiment sucks research propulsive thrust nacelle again asks
Topic has very important realistic meaning.
Claims (2)
1. a kind of propulsive thrust PIV tests high pressure trace particle delivery device, including high pressure trace displaying particle generator pressure duct,
It is characterized in that further including high pressure nozzle and pressure stabilizing sieve pore device, high pressure trace displaying particle generator is connect with high pressure nozzle, high pressure spray
Mouth is connect by pressure duct with pressure stabilizing sieve pore device, and pressure stabilizing sieve pore device sprays the high pressure gas with trace particle.
2. a kind of propulsive thrust PIV according to claim 1 tests high pressure trace particle delivery device, it is characterised in that: institute
The pressure stabilizing sieve pore device stated includes shell and sieve nest, and sieve nest is mounted in shell, and the space between sieve nest and shell is pressure stabilizing cavity,
Multiple sieve pores are provided on sieve nest.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811264867.2A CN109238648A (en) | 2018-10-29 | 2018-10-29 | Propulsive thrust PIV tests high pressure trace particle delivery device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811264867.2A CN109238648A (en) | 2018-10-29 | 2018-10-29 | Propulsive thrust PIV tests high pressure trace particle delivery device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109238648A true CN109238648A (en) | 2019-01-18 |
Family
ID=65078607
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811264867.2A Pending CN109238648A (en) | 2018-10-29 | 2018-10-29 | Propulsive thrust PIV tests high pressure trace particle delivery device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109238648A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111122114A (en) * | 2020-01-08 | 2020-05-08 | 河海大学 | Automatic tracer feeding device for field tracer experiment in subsurface flow zone and implementation method of automatic tracer feeding device |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU2858977A (en) * | 1976-09-07 | 1979-03-15 | Emerson Electric Co | Charged particle apparatus and procedures |
| CN1115001A (en) * | 1994-07-15 | 1996-01-17 | 西安石油勘探仪器总厂 | Radioactive energy spectrum tracing water uptake section well logging method |
| CN201615269U (en) * | 2009-12-24 | 2010-10-27 | 中业阀门集团有限公司 | Reverse-flow internal spray hole depressurizing and pressure-stabilizing valve |
| CN202158945U (en) * | 2011-05-11 | 2012-03-07 | 魏润杰 | Solid-state particle generator |
| CN202628315U (en) * | 2012-04-28 | 2012-12-26 | 宋龙甫 | High-pressure jet mixer of natural gas engine |
| CN103017999A (en) * | 2012-12-07 | 2013-04-03 | 大连海事大学 | Flow field characteristic experiment device of combustion chamber of hydrogen-burning gas turbine |
| CN103321804A (en) * | 2013-05-31 | 2013-09-25 | 哈尔滨工程大学 | Pressure wave damping type voltage stabilizer |
| CN103940573A (en) * | 2014-05-06 | 2014-07-23 | 大连理工大学 | Tracer particle dispensing device and dispensing method for small-size PIV flow field testing experiment |
| CN103969020A (en) * | 2013-08-23 | 2014-08-06 | 中国人民解放军国防科学技术大学 | Supersonic airflow generation system beneficial to uniform scattering of nano particles |
| CN105021367A (en) * | 2015-07-27 | 2015-11-04 | 中国航空工业集团公司哈尔滨空气动力研究所 | Portable tracer particle generator apparatus based on pressure atomization and generation method |
| CN205333292U (en) * | 2016-01-21 | 2016-06-22 | 河海大学 | A tracer particle puts in device for basin is experimental |
| CN106290978A (en) * | 2016-08-25 | 2017-01-04 | 北京航空航天大学 | A kind of transverse injection agitation blends liquid trace displaying particle generator |
| CN207036365U (en) * | 2017-03-31 | 2018-02-23 | 北京汽车研究总院有限公司 | A kind of automobile sealed property test measurement device |
| CN208795453U (en) * | 2018-10-29 | 2019-04-26 | 中国航空工业集团公司哈尔滨空气动力研究所 | Propulsive thrust PIV tests high pressure trace particle delivery device |
-
2018
- 2018-10-29 CN CN201811264867.2A patent/CN109238648A/en active Pending
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU2858977A (en) * | 1976-09-07 | 1979-03-15 | Emerson Electric Co | Charged particle apparatus and procedures |
| CN1115001A (en) * | 1994-07-15 | 1996-01-17 | 西安石油勘探仪器总厂 | Radioactive energy spectrum tracing water uptake section well logging method |
| CN201615269U (en) * | 2009-12-24 | 2010-10-27 | 中业阀门集团有限公司 | Reverse-flow internal spray hole depressurizing and pressure-stabilizing valve |
| CN202158945U (en) * | 2011-05-11 | 2012-03-07 | 魏润杰 | Solid-state particle generator |
| CN202628315U (en) * | 2012-04-28 | 2012-12-26 | 宋龙甫 | High-pressure jet mixer of natural gas engine |
| CN103017999A (en) * | 2012-12-07 | 2013-04-03 | 大连海事大学 | Flow field characteristic experiment device of combustion chamber of hydrogen-burning gas turbine |
| CN103321804A (en) * | 2013-05-31 | 2013-09-25 | 哈尔滨工程大学 | Pressure wave damping type voltage stabilizer |
| CN103969020A (en) * | 2013-08-23 | 2014-08-06 | 中国人民解放军国防科学技术大学 | Supersonic airflow generation system beneficial to uniform scattering of nano particles |
| CN103940573A (en) * | 2014-05-06 | 2014-07-23 | 大连理工大学 | Tracer particle dispensing device and dispensing method for small-size PIV flow field testing experiment |
| CN105021367A (en) * | 2015-07-27 | 2015-11-04 | 中国航空工业集团公司哈尔滨空气动力研究所 | Portable tracer particle generator apparatus based on pressure atomization and generation method |
| CN205333292U (en) * | 2016-01-21 | 2016-06-22 | 河海大学 | A tracer particle puts in device for basin is experimental |
| CN106290978A (en) * | 2016-08-25 | 2017-01-04 | 北京航空航天大学 | A kind of transverse injection agitation blends liquid trace displaying particle generator |
| CN207036365U (en) * | 2017-03-31 | 2018-02-23 | 北京汽车研究总院有限公司 | A kind of automobile sealed property test measurement device |
| CN208795453U (en) * | 2018-10-29 | 2019-04-26 | 中国航空工业集团公司哈尔滨空气动力研究所 | Propulsive thrust PIV tests high pressure trace particle delivery device |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111122114A (en) * | 2020-01-08 | 2020-05-08 | 河海大学 | Automatic tracer feeding device for field tracer experiment in subsurface flow zone and implementation method of automatic tracer feeding device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102582843B (en) | Simulation system for ice-formation condition on ground | |
| CN106988926B (en) | Whirlpool axis turbofan combined cycle engine | |
| CN208795453U (en) | Propulsive thrust PIV tests high pressure trace particle delivery device | |
| CN106050472A (en) | Turbo-rocket combined ramjet engine and operating method thereof | |
| CN104727978A (en) | Working method of superimposed ram rocket | |
| CN103835836A (en) | Bypass-ratio controllable gas turbine | |
| CN104675558A (en) | Stacked suction rocket operation method | |
| CN106762221B (en) | Turbo ramjet engine ram-air turbine heat to electricity conversion and forecooling method | |
| CN104696102A (en) | Working method of rocket capable of generating oxygen through superposition aspiration | |
| CN104775935A (en) | Working method of superposition pressing oxygen production rocket | |
| CN104675561A (en) | Working method of air-breathing rocket | |
| CN103612751A (en) | Air amplification type aircraft propulsion device | |
| CN109238648A (en) | Propulsive thrust PIV tests high pressure trace particle delivery device | |
| CN104675557A (en) | Working method of air-breathing and oxygen generation rocket | |
| CN106168185A (en) | Air turbine punching press combined engine and method of work thereof | |
| CN202670093U (en) | Autogiro capable of taking off and landing vertically | |
| CN103742295A (en) | Turbojet engine and method for mixing liquid gas during operation of turbojet engine | |
| CN107745818B (en) | Aircraft propulsion system and vertical take-off and landing aircraft with same | |
| CN104986323A (en) | Glove vane aircraft | |
| CN104929809A (en) | Working method of detonation ram rocket | |
| CN205592035U (en) | Combined cycle engine | |
| CN203769944U (en) | Liquid gas hybrid turbojet engine | |
| CN104131915A (en) | Ramjet started in static state | |
| CN204060937U (en) | A kind of aeroengine | |
| CN107842423A (en) | The pushing system of water spray or methanol suitable for small-size turbojet 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 |