CN106840594B - A kind of four hole dynamic pressure probes measuring transonic speed three-dimensional non-steady flow field - Google Patents
A kind of four hole dynamic pressure probes measuring transonic speed three-dimensional non-steady flow field Download PDFInfo
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- CN106840594B CN106840594B CN201710126237.8A CN201710126237A CN106840594B CN 106840594 B CN106840594 B CN 106840594B CN 201710126237 A CN201710126237 A CN 201710126237A CN 106840594 B CN106840594 B CN 106840594B
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/062—Wind tunnel balances; Holding devices combined with measuring arrangements
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L23/00—Devices or apparatus for measuring or indicating or recording rapid changes, such as oscillations, in the pressure of steam, gas, or liquid; Indicators for determining work or energy of steam, internal-combustion, or other fluid-pressure engines from the condition of the working fluid
- G01L23/26—Details or accessories
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- General Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
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- Combustion & Propulsion (AREA)
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Abstract
The invention belongs to pressure test technical fields, disclose a kind of four hole dynamic pressure probes for measuring transonic speed three-dimensional non-steady flow field, including end of probe, strut, end of probe is wedge top bicircular arcs prism structure, 4 dynamic pressure transducers of its enclosed inside, the leeward of end of probe is cylinder rear arc, windward side includes wedge top bevel, cylinder front arc, symmetrical left side plane and right side plan, windward side is provided with 4 not connected pressure experience holes, it is connected to respectively with 4 dynamic pressure transducers in end of probe, 4 dynamic pressure transducer cables draw probe tails by probe strut internal channel.Compared with existing pressure probe, measurement subsonic speed and Supersonic Three Dimensional Flow Dynamic Flow Field can be taken into account, the present invention is demarcated by calibration wind tunnel, stagnation pressure, static pressure, deflection angle, pitch angle and the Mach number that transonic flow can be measured change with time, and provide a kind of means for measuring transonic compressor three-dimensional non-steady flow field.
Description
Technical field
The invention belongs to pressure test technical fields, are related to the dynamic pressure measurement dress in transonic speed three-dimensional non-steady flow field
Set, and in particular to it is a kind of measure transonic speed three-dimensional non-steady flow field four hole dynamic pressure probes, be suitable for turbomachine import,
The test in transonic speed Three-Dimensional Dynamic flow field between outlet and grade.
Background technique
Three-dimensional flow field between transonic compressor import, outlet and grade, due to fluid viscosity, shock wave, the rotation of rotor, blade tip
What the presence in gap, rotor and stator blade were arranged is staggered, and is substantially unsteady.It can not using conventional steady state pressure probe
The dynamic characteristic in flow field is measured, hot-wire anemometer can measure dynamic speed signal, but not can be measured pressure information.It is right
In turbine, researcher preferred to obtain between grade, the dynamic pressure distribution of rotor outlet, is examined for verifying design and flow field
It is disconnected, to improve machine performance.
At present due to lacking the technique of dynamic measurement of Practical, generally surveyed using stable states such as five pore pressure force probes in engineering
Amount technology drives pressure probe to go to measured position by the displacement mechanism being mounted on casing, measures transonic speed three-dimensional flow
.Five pore pressure force probe of stable state is since, there are longer pressure guiding pipe, tested flow field has been fallen in the vessel manufacture damping of formation inside it
Dynamic pressure information, true stagnation pressure, static pressure, deflection angle, pitch angle and the Mach number for reflecting tested flow field cannot be obtained at any time
Between changing rule, parameter distribution of the rotor outlet from pressure face to suction surface cannot be measured.
Summary of the invention
The technical problem to be solved by the present invention is being directed in current engineering three between transonic compressor import, outlet and grade
It ties up Unsteady Flow measurement means and lacks problem, invent a kind of four hole dynamic pressures spy for measuring transonic speed three-dimensional non-steady flow field
Needle, high subsonic speed three-dimensional non-steady flow field can accurately be measured and be taken into account within the scope of wider direction of flow by providing one kind
The effectively technological means of measurement Supersonic Three Dimensional Flow Unsteady Flow.
The technical solution of the invention is as follows:
A kind of four hole dynamic pressure probes measuring transonic speed three-dimensional non-steady flow field, it is characterised in that: including probe
Portion (1), strut (2), the end of probe (1) are wedge top bicircular arcs prism structure, 4 dynamic pressure sensings of enclosed inside
Device, end of probe (1) windward side when probe measures includes the wedge top bevel (3) of wedge top bicircular arcs prism, cylinder front arc
(4), symmetrical left side plane (5) and right side plan (6), leeward are cylinder rear arc (7)；Cylinder rear arc (7) and cylinder
Front arc (4) is the side of same cylinder, which is overlapped with the axis of strut (2)；It is oblique on the wedge top of end of probe (1)
Face (3), left side (5), is respectively provided with 1 pressure experience hole on right side (6) at cylinder front arc (4), respectively upper hole (8), in
Hole (9), left hole (10), right hole (11), this 4 not connected pressure experience holes are dynamic with 4 in end of probe (1) respectively
The connection of state pressure sensor.
2, further, probe strut (2) be cylindrical body, inside be provided with round pipeline.
3, further, the angle of end of probe (1) wedge top bevel (3) and strut (2) axis is 36 ° to 54 °.
4, further, pressure experience hole (8) center line, pressure experience hole (9) center line and strut (2) axis are same
In plane, left side (5), right side (6) are symmetrical along the plane, and left side (5), right side (6) angle are 30 ° to 70 °.
5, further, the left hole (10) and right hole (11) on end of probe (1) are along mesoporous (9) center line and upper hole (8)
Plane where heart line is symmetrical.
6, further, upper hole (8) center of circle of end of probe (1) is 1 millimeter at a distance from wedge top bevel (3) circular arc minimum point
To 5 millimeters.
7, further, mesoporous (9) center of circle of end of probe (1) is 1 millimeter at a distance from wedge top bevel (3) circular arc minimum point
To 3 millimeters.
8, further, the diameter in (1) 4 pressure experience hole of end of probe is 0.6 millimeter to 1.5 millimeters.
9, further, the arc diameter of end of probe (1) wedge top bicircular arcs prism structure is 4 millimeters to 8 millimeters, prism knot
Structure is 15 millimeters to 50 millimeters high.
10, the cable (12) of 4 dynamic pressure transducers further, encapsulated in end of probe (1) passes through probe strut
(2) pipeline in draws probe tails.
The beneficial effects of the present invention are:
Compared with existing pressure probe, measurement subsonic speed and Supersonic Three Dimensional Flow Dynamic Flow Field can be taken into account, the present invention passes through
Calibration wind tunnel calibration, stagnation pressure, static pressure, deflection angle, pitch angle and the Mach number that can measure transonic flow change with time, provide
A kind of means measuring transonic compressor three-dimensional non-steady flow field.
Detailed description of the invention
Fig. 1 is the knot of the four hole dynamic pressure probes in the measurement transonic speed three-dimensional non-steady flow field in the embodiment of the present invention
Structure schematic diagram.
Fig. 2 is the left view of Fig. 1.
Fig. 3 is the A direction view of Fig. 2.
Wherein: 1- end of probe, 2- probe strut, 3- wedge top bevel, 4- cylinder front arc, 5- left side plane, the right side 6-
Plane, 7- cylinder rear arc, the upper hole 8-, 9- mesoporous, 10- left hole, 11- right hole, 12- cable.
Specific embodiment
The present invention will be described in detail in the following with reference to the drawings and specific embodiments.
As shown in Figure 1, describing a kind of four hole dynamic pressures for measuring transonic speed three-dimensional non-steady flow field in the present embodiment
Probe, including end of probe (1) and strut (2), end of probe (1) are wedge top bicircular arcs prism structure, and circumscribed circle diameter is 6 millis
Rice, end of probe (1) is 30 millimeters high, 4 dynamic pressure transducers of enclosed inside, and the end of probe (1) when probe measures is met
Wind face includes wedge top bevel (3), cylinder front arc (4), symmetrical left side plane (5) and the right side plan of wedge top bicircular arcs prism
(6), leeward is cylinder rear arc (7)；Cylinder rear arc (7) and cylinder front arc (4) are the side of same cylinder, the cylinder
Axis is overlapped with the axis of strut (2)；On the wedge top bevel (3) of end of probe (1), cylinder front arc (4), left side (5), the right side
1 pressure experience hole is respectively provided on side (6), respectively upper hole (8), mesoporous (9), left hole (10), right hole (11), this 4 mutually
The pressure experience hole being not communicated with is connected to 4 dynamic pressure transducers in end of probe (1) respectively.
Probe strut (2) is cylindrical body, 8 millimeters of diameter, inside be provided with round channel, 5 millimeters of diameter.
The angle of end of probe (1) wedge top bevel (3) and strut (2) axis is 40 °.
Pressure experience hole (8) center line, pressure experience hole (9) center line and strut (2) axis are in the same plane, left
Side (5), right side (6) are symmetrical along the plane, and left side (5), right side (6) angle are 40 °.
Left hole (10) and right hole (11) on end of probe (1) is where mesoporous (9) center line and upper hole (8) center line
Plane is symmetrical.The center of circle of left hole (10), right hole (11) and mesoporous (9) in the same plane, left hole (10) center of circle and cylinder
The distance on front arc (4) left side be 3 millimeters, right hole (11) center of circle with cylinder front arc (4) on the right of at a distance from be 3 millimeters.
Upper hole (8) center of circle of end of probe (1) is 2 millimeters at a distance from wedge top bevel (3) circular arc minimum point.
Mesoporous (9) center of circle of end of probe (1) is 2 millimeters at a distance from wedge top bevel (3) circular arc minimum point.
The diameter in (1) 4 pressure experience hole of end of probe is 0.6 millimeter.
The cable (12) of 4 dynamic pressure transducers encapsulated in end of probe (1) passes through the pipeline in probe strut (2)
Draw probe tails.
The four hole dynamic pressure probes in the measurement transonic speed three-dimensional non-steady flow field introduced in the embodiment of the present invention, by across
The calibration of velocity of sound calibration wind tunnel, can obtain nominal data.When actual measurement transonic speed three-dimensional non-steady flow field, four hole dynamic is pressed
4 dynamic pressure transducers of force probe measure the unsteady pressure data respectively experienced simultaneously, utilize the transonic speed of acquisition
Calibration wind tunnel nominal data carries out data processing, can obtain the stagnation pressure of across sound three-dimensional non-steady incoming flow, static pressure, deflection angle, bow
The elevation angle and Mach number change with time.
Claims (1)
1. a kind of four hole dynamic pressure probes for measuring transonic speed three-dimensional non-steady flow field, it is characterised in that: including end of probe
(1), strut (2), the end of probe (1) be wedge top bicircular arcs prism structure, 4 dynamic pressure transducers of enclosed inside,
End of probe (1) windward side when probe measures includes the wedge top bevel (3) of wedge top bicircular arcs prism, cylinder front arc (4), right
The left side plane (5) and right side plan (6) of title, leeward are cylinder rear arc (7)；Cylinder rear arc (7) and cylinder front arc
It (4) is the side of same cylinder, which is overlapped with the axis of strut (2)；End of probe (1) wedge top bevel (3),
Cylinder front arc (4), left side plane (5) are respectively provided with 1 pressure experience hole on right side plan (6), respectively upper hole (8), mesoporous
(9), left hole (10), right hole (11), this 4 not connected pressure experience holes, respectively with 4 dynamics in end of probe (1)
Pressure sensor connection；
The strut (2) be cylindrical body, inside be provided with round pipeline；
The angle of end of probe (1) the wedge top bevel (3) and strut (2) axis is 40 °；
Upper hole (8) center line, mesoporous (9) center line and strut (2) axis are in the same plane, left side plane (5), right
Side plane (6) is symmetrical along the plane, and left side plane (5), right side plan (6) angle are 40 °；
Left hole (10) and right hole (11) on the end of probe (1) is where mesoporous (9) center line and upper hole (8) center line
Plane is symmetrical；
Hole (8) center of circle and wedge top bevel (3) circular arc perigee distance are 2 millimeters on the end of probe (1)；
End of probe (1) mesoporous (9) center of circle and wedge top bevel (3) circular arc perigee distance are 2 millimeters；
The diameter in (1) 4 pressure experience hole of end of probe is 0.6 millimeter；
The arc diameter of end of probe (1) wedge top bicircular arcs prism structure is 4 millimeters to 8 millimeters, high 15 milli of prism structure
Rice is to 50 millimeters；
The cable (12) of 4 dynamic pressure transducers encapsulated in the end of probe (1) is drawn by the pipeline in strut (2)
Probe tails.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710126237.8A CN106840594B (en) | 2017-03-06 | 2017-03-06 | A kind of four hole dynamic pressure probes measuring transonic speed three-dimensional non-steady flow field |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710126237.8A CN106840594B (en) | 2017-03-06 | 2017-03-06 | A kind of four hole dynamic pressure probes measuring transonic speed three-dimensional non-steady flow field |
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| Publication Number | Publication Date |
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| CN106840594A CN106840594A (en) | 2017-06-13 |
| CN106840594B true CN106840594B (en) | 2019-11-12 |
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| CN111473909B (en) * | 2020-03-23 | 2022-02-08 | 南京航空航天大学 | Pressure sensor system for measuring outlet pressure of compressor |
Citations (4)
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|---|---|---|---|---|
| US5929331A (en) * | 1997-01-14 | 1999-07-27 | The Texas A&M University System | Multi-directional, three component velocity measurement pressure probe |
| CN203940946U (en) * | 2014-07-04 | 2014-11-12 | 北京航空航天大学 | A kind of five-hole probe for full flow directional detection |
| CN204694444U (en) * | 2015-06-01 | 2015-10-07 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of probe assembly and there is its device |
| CN105716788A (en) * | 2015-11-02 | 2016-06-29 | 北京航空航天大学 | Three-hole transonic speed pressure probe |
-
2017
- 2017-03-06 CN CN201710126237.8A patent/CN106840594B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5929331A (en) * | 1997-01-14 | 1999-07-27 | The Texas A&M University System | Multi-directional, three component velocity measurement pressure probe |
| CN203940946U (en) * | 2014-07-04 | 2014-11-12 | 北京航空航天大学 | A kind of five-hole probe for full flow directional detection |
| CN204694444U (en) * | 2015-06-01 | 2015-10-07 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of probe assembly and there is its device |
| CN105716788A (en) * | 2015-11-02 | 2016-06-29 | 北京航空航天大学 | Three-hole transonic speed pressure probe |
Non-Patent Citations (3)
| Title |
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| 《基于数字信号处理功能实现的动态探针研制》;姚君;《中国优秀硕士学位论文全文数据库工程科技II辑》;20110215(第2期);第C028-1页 * |
| 《楔顶双孔探针测量跨声多级压气机转子出口三维动态流场的方法》;李井洋等;《航空动力学报》;20121031;第27卷(第10期);第2262-2268页 * |
| 《跨音速气体动力探针的实验研究》;蒋培正等;《跨音速气体动力探针的实验研究》;19850228;第19卷(第1期);第1-10页 * |
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