CN106885683A - A kind of hole steady state pressure probe of hemispherical head 12 for measuring 3 D complex flow field - Google Patents
A kind of hole steady state pressure probe of hemispherical head 12 for measuring 3 D complex flow field Download PDFInfo
- Publication number
- CN106885683A CN106885683A CN201710132968.3A CN201710132968A CN106885683A CN 106885683 A CN106885683 A CN 106885683A CN 201710132968 A CN201710132968 A CN 201710132968A CN 106885683 A CN106885683 A CN 106885683A
- Authority
- CN
- China
- Prior art keywords
- probe
- pressure
- cylinder
- hole
- millimeters
- 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.)
- Granted
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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
Abstract
The invention belongs to pressure test technical field, disclose a kind of hole steady state pressure probe of hemispherical head 12 for measuring 3 D complex flow field, including end of probe and pole, end of probe is made up of bottom surface altogether cylinder and hemisphere, 8 pressure experience holes are provided with the end of probe face of cylinder, 4 pressure experience holes are provided with hemisphere surface, this 12 pressure experience holes connect with 12 pressure guiding pipes in end of probe respectively, 12 pressure guiding pipes draw probe tails by probe pole internal channel.Compared with existing pressure probe, the present invention is by demarcating, can measure to flow deflection angle ± 180 °, stagnation pressure, static pressure, Mach number, the angle of pitch, deflection angular dimensions in the range of the angle of pitch ± 30 ° simultaneously, it is adaptable to measure aero-engine, compressor, fan etc. and forcing the process Leaf of breathing heavily to discharge into the 3 D complex flow field for existing between mouth, outlet, level and flowing back.
Description
Technical field
The invention belongs to pressure test technical field, it is related to the dynamic pressure measurement device in three-dimensional non-steady flow field, specifically
It is related to a kind of hole steady state pressure probe of hemispherical head 12 for measuring 3 D complex flow field, it is adaptable to measure aero-engine, calm the anger
Machine, fan etc. are forcing the process Leaf of breathing heavily to discharge into the 3 D complex flow field that there is backflow between mouth, outlet, level, are also applied for measurement
Direction of flow is not clear, direction of flow is changed greatly, probe cannot adjust setting angle, there is the 3 D complex stream of backflow after installing
.
Background technology
Pressure probe, such as five pore pressure force probes, seven apertures in the human head pressure probe, with its simple structure, durable, easily operated
The advantages of be widely used in the measurement of the interior three-dimensional flow field such as aero-engine, gas turbine, compressor, blower fan, pump.Due to structure and
The limitation of aerodynamic characteristic, the scope of five pore pressure force probe measurement directions of flow is restricted, and deflection angle is usually no more than ± 45 °,
The measurement of seven apertures in the human head pressure probe is also no more than ± 70 ° come the deflection angle ranges for flowing.
In the flow field that measurement direction of flow is not clear, if these probes do not have rough alignment direction of flow when installing, exceed
The effective angular surveying scope of probe, then although obtaining data from pressure experience hole measurement, cannot calculate airflow direction,
The flow parameters such as stagnation pressure, static pressure.
Aero-engine, compressor, fan etc. are forced during breathing heavily, and blade discharges into three-dimensional flow field between mouth, outlet or blade row
In the presence of backflow, five conventional pore pressure force probes or seven apertures in the human head pressure probe cannot accurately measure flow-deviation angle, the pitching in the region
Angle, stagnation pressure, static pressure, Mach number, lack the three-dimensional steady state pressure probe technology that can take into account measurement backflow of Practical at present.
The content of the invention
The technical problem to be solved in the present invention is：For three stability maintenances that can take into account measurement backflow for lacking Practical at present
State pressure probe technology, invents a kind of hole steady state pressure probe of hemispherical head 12 for measuring 3 D complex flow field, can measure and sail
The deflection angle of air-flow when the imports such as empty engine, compressor, fan, outlet or blade have backflow between arranging, the angle of pitch, stagnation pressure,
The steady state datas such as static pressure, Mach number.
Technical solution of the invention is：
1st, a kind of hole steady state pressure probe of hemispherical head 12 for measuring 3 D complex flow field, it is characterised in that：Including probe
Head (1) and pole (2), cylinder (3) of the end of probe (1) including common bottom surface, hemisphere (4), in end of probe circle
8 not connected face of cylinder pressure experience holes (5) are provided with cylinder (3) side, 4 are provided with hemisphere (4) side mutually
The sphere pressure experience hole (6) being not communicated with, 12 pressure experience holes are encapsulated in end of probe (1) with 12 pressure guiding pipes (7) respectively
Interior one end each communicates.
2nd, further, probe pole (2) is cylinder, and 12 of encapsulation in round pipeline, end of probe (1) are provided with inside it
Root pressure guiding pipe (7), probe tails are drawn by the pipeline in probe pole (2).
3rd, further, 8 faces of cylinder pressure experience hole (5) diameter being provided with end of probe (1) cylinder (3) side
Be 0.5 millimeter to 1.5 millimeters, the centerlines in adjacent 2 holes are 45 °, this 8 center lines in hole in approximately the same plane,
The plane, perpendicular to the axis of end of probe (1) cylinder (3), is 1 milli with the distance of end of probe (1) hemisphere (4) bottom surface
Rice is to 5 millimeters.
4th, further, on end of probe (1) hemisphere (4) side, 4 sphere pressure experience holes are circumferentially uniformly provided with
(6), a diameter of 0.5 millimeter to 1.5 millimeters, the center line cylinder corresponding with underface in each sphere pressure experience hole (6)
(3) normal pressure on side experiences the axis of the center line of hole (5), end of probe (1) cylinder (3) in a plane
On, sphere pressure experience hole (6) center of circle is 2 millimeters to 6 millimeters with the distance of hemisphere (4) bottom surface circular arc.
5th, further, a diameter of 6 millimeters to 10 millimeters of the cylinder (3) of end of probe (1), 10 millimeters long to 40 millis
Rice, end of probe (1) cylinder (3) axis overlaps with probe pole (2) axis.
The beneficial effects of the invention are as follows：
Compared with existing pressure probe, the present invention by calibration demarcate, can measure simultaneously flow deflection angle ± 180 °,
The steady state datas such as stagnation pressure, static pressure, Mach number, the angle of pitch, deflection angle in the range of the angle of pitch ± 30 °, it is adaptable to measure aviation hair
Motivation, compressor, fan etc. force the process Leaf of breathing heavily to discharge into the 3 D complex flow field that there is backflow between mouth, outlet, level, are also suitable
In measurement direction of flow it is not clear, direction of flow is changed greatly, probe install after cannot adjust setting angle, there is the three-dimensional of backflow
Complex flowfield.
Brief description of the drawings
Fig. 1 is the structure of 12 pore pressure force probes of the measurement 3 D complex flow field Steady-state Parameters in the embodiment of the present invention one
Schematic diagram.
Fig. 2 is three-dimensional flow field flows the definition schematic diagram of deflection angle, the angle of pitch.
Wherein：1- end of probes, 2- probe poles, 3- cylinders, 4- hemispheres, 5- faces of cylinder pressure experience hole, 6- balls
Surface pressure experiences hole, 7- pressure guiding pipes.
Specific embodiment
The present invention will be described in detail with specific embodiment below in conjunction with the accompanying drawings.
As shown in figure 1, describing a kind of hole stable state pressure of hemispherical head 12 for measuring 3 D complex flow field in the present embodiment one
Force probe, including end of probe (1) and pole (2), cylinder (3) of the end of probe (1) including common bottom surface, hemisphere (4),
8 not connected face of cylinder pressure experience holes (5) are provided with end of probe cylinder (3) side, on hemisphere (4) side
4 not connected sphere pressure experience holes (6) are provided with, 12 pressure experience holes are encapsulated in spy with 12 pressure guiding pipes (7) respectively
One end in needle section (1) each communicates.
Probe pole (2) is cylinder, and 10 millimeters of diameter is provided with round passage, 8 millimeters of diameter, end of probe inside it
(1) 12 pressure guiding pipes (7) of encapsulation in, probe tails are drawn by the pipeline in probe pole (2).
A diameter of 0.5 milli in 8 faces of cylinder pressure experience hole (5) being provided with end of probe (1) cylinder (3) side
Rice, the centerlines in adjacent 2 holes are 45 °, and in approximately the same plane, the plane is perpendicular to probe for this 8 center lines in hole
The axis of head (1) cylinder (3), is 1 millimeter with the distance of end of probe (1) hemisphere (4) bottom surface.
On end of probe (1) hemisphere (4) side, 4 sphere pressure experience holes (6), diameter are circumferentially uniformly provided with
It it is 0.5 millimeter, on center line cylinder (3) side corresponding with underface in each sphere pressure experience hole (6) is just
The center line in pressure experience hole (5), the axis of end of probe (1) cylinder (3) in one plane, sphere pressure experience hole
(6) center of circle and the distance of hemisphere (4) bottom surface circular arc are 2 millimeters.
A diameter of 8 millimeters of the cylinder (3) of end of probe (1), long 30 millimeters, end of probe (1) cylinder (3) axis
Overlapped with probe pole (2) axis.
A kind of hole steady state pressure probe of hemispherical head 12 in the measurement 3 D complex flow field introduced in the embodiment of the present invention, warp
Cross calibration to demarcate, nominal data can be obtained.During actual measurement 3 D complex flow field, the hole steady state pressure probe of hemispherical head 12
12 pressure experience holes measure each pressure data for experiencing, using the nominal data for obtaining, carry out data processing, can survey
Three-dimensional flow stagnation pressure in the range of deflection angle ± 180 °, the angle of pitch ± 30 °, static pressure, Mach number, the angle of pitch, deflection angle
Steady state data, it is adaptable to measure aero-engine, compressor, fan etc. and force the process Leaf of breathing heavily to discharge between mouth, outlet, level three
Dimension complex flowfield, is also applied for that measurement direction of flow is not clear, direction of flow is changed greatly, probe cannot adjust established angle after installing
Spend, exist the 3 D complex flow field of backflow.
Claims (5)
1. a kind of hole steady state pressure probe of hemispherical head 12 for measuring 3 D complex flow field, it is characterised in that：Including end of probe
(1), pole (2), cylinder (3) of the end of probe (1) including common bottom surface, hemisphere (4), in end of probe cylinder
(3) 8 not connected face of cylinder pressure experience holes (5) are provided with side, 4 mutual not phases is provided with hemisphere (4) side
Logical sphere pressure experience hole (6), 12 pressure experience holes are encapsulated in end of probe (1) with 12 pressure guiding pipes (7) respectively
One end each communicates.
2. a kind of hole steady state pressure probe of hemispherical head 12 for measuring 3 D complex flow field according to claim 1, it is special
Levy and be：Probe pole (2) is cylinder, and 12 pressure guiding pipes of encapsulation in round pipeline, end of probe (1) are provided with inside it
(7) probe tails, are drawn by the pipeline in probe pole (2).
3. a kind of hole steady state pressure probe of hemispherical head 12 for measuring 3 D complex flow field according to claim 1, it is special
Levy and be：, a diameter of 0.5 millimeter of 8 faces of cylinder pressure experience hole (5) being provided with end of probe (1) cylinder (3) side
To 1.5 millimeters, the centerlines in adjacent 2 holes are 45 °, and this 8 center lines in hole are in approximately the same plane, and the plane is vertical
It it is 1 millimeter to 5 millimeters with the distance of end of probe (1) hemisphere (4) bottom surface in the axis of end of probe (1) cylinder (3).
4. a kind of hole steady state pressure probe of hemispherical head 12 for measuring 3 D complex flow field according to claim 1, it is special
Levy and be：On end of probe (1) hemisphere (4) side, 4 sphere pressure experience holes (6) are circumferentially uniformly provided with, it is a diameter of
0.5 millimeter to 1.5 millimeters, on center line cylinder (3) side corresponding with underface in each sphere pressure experience hole (6)
One normal pressure experience the center line of hole (5), end of probe (1) cylinder (3) axis in one plane, sphere feeling of stress
It it is 2 millimeters to 6 millimeters by the distance of hole (6) center of circle and hemisphere (4) bottom surface circular arc.
5. a kind of hole steady state pressure probe of hemispherical head 12 for measuring 3 D complex flow field according to claim 1, it is special
Levy and be：A diameter of 6 millimeters to 10 millimeters of the cylinder (3) of end of probe (1), long 10 millimeters to 40 millimeters, end of probe
(1) cylinder (3) axis overlaps with probe pole (2) axis.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710132968.3A CN106885683B (en) | 2017-03-08 | 2017-03-08 | Hemispherical head twelve-hole steady-state pressure probe for measuring three-dimensional complex flow field |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710132968.3A CN106885683B (en) | 2017-03-08 | 2017-03-08 | Hemispherical head twelve-hole steady-state pressure probe for measuring three-dimensional complex flow field |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106885683A true CN106885683A (en) | 2017-06-23 |
| CN106885683B CN106885683B (en) | 2020-04-28 |
Family
ID=59179724
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710132968.3A Active CN106885683B (en) | 2017-03-08 | 2017-03-08 | Hemispherical head twelve-hole steady-state pressure probe for measuring three-dimensional complex flow field |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106885683B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112098040A (en) * | 2020-11-18 | 2020-12-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Measuring device and measuring method for mounting angle of directional dynamic pressure probe |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2108926U (en) * | 1991-12-12 | 1992-07-01 | 清华大学 | Omnibearing tow-dimensional speed measurer of air stream |
| KR20040010185A (en) * | 2002-07-16 | 2004-01-31 | 니혼 서보 가부시키가이샤 | Permanent Magnet Type Rotating Electric Machine |
| US20060288573A1 (en) * | 2004-10-07 | 2006-12-28 | Mitsuyoshi Aizawa | Fluororesin thin film diaphragm pressure sensor and method of fabricating the same |
| KR20110125504A (en) * | 2010-05-13 | 2011-11-21 | 한양대학교 산학협력단 | Anemovane |
| CN102636662A (en) * | 2012-04-20 | 2012-08-15 | 南京航空航天大学 | Full-flow direction flow velocity measurement probe and measurement method thereof |
| CN104155473A (en) * | 2014-08-12 | 2014-11-19 | 南京航空航天大学 | Wind speed and wind direction sensing device |
| CN204330280U (en) * | 2015-01-18 | 2015-05-13 | 中南大学 | Train parting flow field on-site testing device |
| CN204944736U (en) * | 2015-09-16 | 2016-01-06 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of total pressure measurement probe |
| CN105588703A (en) * | 2015-12-15 | 2016-05-18 | 中国燃气涡轮研究院 | 12-hole omni-directional probe for subsonic-speed and complex three-dimensional flow field measurement |
| CN106290968A (en) * | 2016-09-14 | 2017-01-04 | 华北电力科学研究院(西安)有限公司 | A kind of large space pulsatile flow field three-dimension measuring system and measuring method |
-
2017
- 2017-03-08 CN CN201710132968.3A patent/CN106885683B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2108926U (en) * | 1991-12-12 | 1992-07-01 | 清华大学 | Omnibearing tow-dimensional speed measurer of air stream |
| KR20040010185A (en) * | 2002-07-16 | 2004-01-31 | 니혼 서보 가부시키가이샤 | Permanent Magnet Type Rotating Electric Machine |
| US20060288573A1 (en) * | 2004-10-07 | 2006-12-28 | Mitsuyoshi Aizawa | Fluororesin thin film diaphragm pressure sensor and method of fabricating the same |
| KR20110125504A (en) * | 2010-05-13 | 2011-11-21 | 한양대학교 산학협력단 | Anemovane |
| CN102636662A (en) * | 2012-04-20 | 2012-08-15 | 南京航空航天大学 | Full-flow direction flow velocity measurement probe and measurement method thereof |
| CN104155473A (en) * | 2014-08-12 | 2014-11-19 | 南京航空航天大学 | Wind speed and wind direction sensing device |
| CN204330280U (en) * | 2015-01-18 | 2015-05-13 | 中南大学 | Train parting flow field on-site testing device |
| CN204944736U (en) * | 2015-09-16 | 2016-01-06 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of total pressure measurement probe |
| CN105588703A (en) * | 2015-12-15 | 2016-05-18 | 中国燃气涡轮研究院 | 12-hole omni-directional probe for subsonic-speed and complex three-dimensional flow field measurement |
| CN106290968A (en) * | 2016-09-14 | 2017-01-04 | 华北电力科学研究院(西安)有限公司 | A kind of large space pulsatile flow field three-dimension measuring system and measuring method |
Non-Patent Citations (2)
| Title |
|---|
| DODSON, KIRSTEN H.: "《a microfluidic platform for point access signaling studies》", 《BIOMED MICRODEVICES》 * |
| 姚君: "基于数字信号处理功能实现的动态探针研制", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112098040A (en) * | 2020-11-18 | 2020-12-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Measuring device and measuring method for mounting angle of directional dynamic pressure probe |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106885683B (en) | 2020-04-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102692310B (en) | Three-hole probe type pressure measurement tail rake for wind tunnel test | |
| CN109506744B (en) | Air flow calibration method for venturi nozzle of aircraft engine complete machine test | |
| CN106989895A (en) | A kind of 12 hole dynamic pressure probes for measuring three-dimensional non-steady complex flowfield | |
| CN103411769B (en) | For the air inlet stable-pressure device of gas-turbine unit swirler performance test | |
| CN107917793A (en) | The multiple rows of pressure measurement rake device of one kind experiment | |
| CN105659063A (en) | Air pressure probe | |
| CN106908185A (en) | A kind of pore pressure force probe of hemispherical head five is combed | |
| CN106768824A (en) | A kind of three pore pressure force probes comb | |
| CN106949989A (en) | A kind of hemispherical head steady temperature force combination probe for measuring low speed three-dimensional flow field | |
| CN106885683A (en) | A kind of hole steady state pressure probe of hemispherical head 12 for measuring 3 D complex flow field | |
| CN106932139B (en) | Four-hole pressure leaf-shaped probe | |
| CN106989896A (en) | A kind of dynamic temperature force combination probe for measuring subsonics three-dimensional non-steady flow field | |
| CN106525159A (en) | Air flow measurement device | |
| CN106768597A (en) | A kind of cylinder single hole dynamic pressure probe for measuring rotor outlet two-dimensional flow field | |
| CN106871968A (en) | One kind measurement subsonic speed flow field multiple spot stagnation temperature stagnation pressure octal probe | |
| CN106950003A (en) | A kind of dynamic pressure probe of circular cone single hole for measuring rotor outlet across sound three-dimensional flow field | |
| CN211904600U (en) | False tail branch for measuring internal resistance of ventilation model | |
| CN106932165A (en) | A kind of pore pressure force probe of round platform five is combed | |
| CN107036818A (en) | A kind of three pore pressure force blade profile probes | |
| CN106768598A (en) | It is a kind of measure blade arrange between stagnation pressure along leaf distribution high the porous total pressure probe of cylinder | |
| CN107063696B (en) | Five-hole pressure leaf-shaped probe | |
| CN106940241A (en) | A kind of steady temperature force combination probe for measuring transonic speed three-dimensional flow field | |
| CN106940240A (en) | A kind of circular cone diplopore dynamic pressure probe for measuring rotor outlet across sound three-dimensional flow | |
| CN206177381U (en) | Wind channel flow measuring device | |
| CN112546367A (en) | Differential pressure type flow sensor and breathing machine |
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 |