CN106768826A - A kind of dynamic temperature force combination probe for measuring Supersonic Two Dimensional Unsteady flow field - Google Patents
A kind of dynamic temperature force combination probe for measuring Supersonic Two Dimensional Unsteady flow field Download PDFInfo
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- CN106768826A CN106768826A CN201710126813.9A CN201710126813A CN106768826A CN 106768826 A CN106768826 A CN 106768826A CN 201710126813 A CN201710126813 A CN 201710126813A CN 106768826 A CN106768826 A CN 106768826A
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- probe
- dynamic temperature
- flow field
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- unsteady flow
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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
Abstract
The invention belongs to temperature, pressure test technical field, disclose a kind of dynamic temperature force combination probe for measuring Supersonic Two Dimensional Unsteady flow field, including end of probe, pole, end of probe is wedge column structure, built with 3 dynamic pressure transducers, 1 dynamic temperature sensor.End of probe windward side includes left surface, right flank during measurement, and lee face is cylinder cambered surface.Leading edge in left and right side and two sides boundary respectively has 1 pressure experience hole, is connected with 3 dynamic pressure transducers in end of probe respectively, and dynamic temperature sensor head exposes end of probe top surface, and sensor wire draws probe tails by pole internal channel.Compared with existing pressure probe, the present invention is demarcated by calibration wind tunnel, Supersonic temperature of incoming flow, stagnation pressure, static pressure, deflection angle, Mach number and two-dimension speed can simultaneously be measured to change with time, for turbine experiment provides a kind of means for measuring Supersonic Two Dimensional Unsteady flow field parameter efficiently, accurately, comprehensively.
Description
Technical field
The invention belongs to temperature, pressure test technical field, it is related to the dynamic temperature in supersonic speed Two Dimensional Unsteady flow field, moves
A kind of state device for pressure measurement, and in particular to dynamic temperature force combination probe in measurement Supersonic Two Dimensional Unsteady flow field, is applicable
The test of supersonic speed two dimension Dynamic Flow Field between aero-engine supersonic inlet, turbomachine import, outlet and level.
Background technology
Aero-engine, the turbine inlet of gas turbine carry out stream and there is hot spot that downstream thermo parameters method can be influenceed, or even sternly
Ghost image rings turbo blade thermic load and life-span.The mechanism of transmission of the research hot spot between nozzle ring, level is led, it is necessary to measure turbine
To the unsteady velocity field of device outlet supersonic speed two-dimensional flow field, pressure field and temperature field.
Three pore pressure force probes, stagnation temperature probe is typically respectively adopted at present, by the displacement mechanism on casing, drives
Probe goes to measured position, measures.Three pore pressure force probes can only provide to flow stagnation pressure, static pressure, deflection angle and Mach number, always
Warm probe can only provide stagnation temperature data.
Experimental study is carried out using existing probe measurement technique, be there are problems that following：1st, two kinds of probes are surveyed respectively
Amount, test period is long, and experimentation cost is high；2nd, two kinds of probes are measured respectively, need to change probe in process of the test to flow operating mode meeting
There is certain change, especially temperature field can be inconsistent；3rd, influenceed can by displacement mechanism positioning for the point position of different probe
Can it is variant, the flow parameter data that different probe is measured certainly not from same streamline, using these probe measurements
Data, when combination calculates the parameters such as speed, can bring about data error, and then can bring very important to total measurement result
Error；4th, due to the rotation of turbine rotor blade, nozzle ring outlet supersonic speed two-dimensional flow field is unsteady, with movable vane leaf
The change of piece position and change, existing probe technique can only provide pressure, temperature and the speed data of stable state, it is impossible to reflection heat
The unsteady mechanism of transmission of the spot in turbine.
The content of the invention
The purpose of the present invention is directed to hot spot in turbine supersonic speed two dimension Dynamic Flow Field propagation test, existing probe skill
Art can not simultaneously provide dynamic pressure, dynamic temperature and the dynamic speed data problem in tested flow field, a kind of measurement Supersonic of invention
The dynamic temperature force combination probe in Two Dimensional Unsteady flow field, can simultaneously measure nozzle ring outlet supersonic speed two-dimensional flow field
Temperature, stagnation pressure, static pressure, deflection angle, Mach number and speed change with time, it is adaptable to study hot spot in nozzle ring, level
Between the unsteady mechanism of transmission.
Technical solution of the invention is：
1st, a kind of dynamic temperature force combination probe for measuring Supersonic Two Dimensional Unsteady flow field, it is characterised in that：Including visiting
Needle section (1), pole (2), the end of probe (1) is wedge column structure, and it is internal equipped with 3 dynamic pressure transducers, 1
Branch dynamic temperature sensor, top surface (3) is vertical with probe pole (2) rotation axis, and end of probe (1) windward side is point during measurement
Split, including symmetrical left surface (4) and right flank (5), lee face is cylinder cambered surface (6)；End of probe (1) left surface (4),
1 pressure experience hole, respectively left hole (7), right hole (8), mesopore are respectively provided with the leading edge of right flank (5) and two sides boundary
(9), this 3 not connected pressure experience holes, connect with 3 dynamic pressure transducers in probe respectively；Dynamic temperature is passed
Sensor head (10) exposes top surface (3).
2nd, further, probe pole (2) is column structure, can be cylinder, or triangular prism, is provided with inside it
Circular channel.
3rd, further, dynamic temperature sensor head (10) exposes (3) 1 millimeters to 5 millimeters of top surface.
4th, further, end of probe (1) left surface (4), right flank (5) angle are 30 ° to 60 °.
5th, further, end of probe (1) left surface (4) have a common boundary with right flank (5) costa, dynamic temperature sensor head
In approximately the same plane, left surface (4), right flank (5) are along the plane symmetry, left hole for portion (10) center line, mesopore (9) center line
(7) it is distributed along the plane symmetry with right hole (8).
6th, further, mesopore (9) center of circle and the distance of end of probe (1) top surface (3) are 1 millimeter to 5 millimeters.
7th, further, left hole (7), right hole (8), a diameter of 0.6 millimeter to 1.5 millimeters of mesopore (9).
8th, further, the cable (11) of dynamic pressure transducer and dynamic temperature sensor through probe pole (2) internal channel,
Drawn by probe tails.
The beneficial effects of the invention are as follows：
Compared with existing pressure probe, the present invention is demarcated by calibration wind tunnel, can simultaneously measure Supersonic temperature of incoming flow, total
Pressure, static pressure, deflection angle, Mach number and two-dimension speed change with time, for turbine experiment provide it is a kind of efficiently, accurately,
The means of Supersonic Two Dimensional Unsteady flow field parameter are measured comprehensively.
Brief description of the drawings
Fig. 1 is the dynamic temperature force combination probe in the measurement Supersonic Two Dimensional Unsteady flow field in embodiments of the invention
Structural representation.
Fig. 2 is the left view of Fig. 1.
Fig. 3 is the top view of Fig. 1.
Wherein：1- end of probes, 2- probe poles, 3- top surfaces, 4- left surfaces, 5- right flanks, 6- cylinder cambered surfaces, 7- is left
Hole, 8- right hole, 9- mesopores, 10- dynamic temperature sensor heads, 11- cables.
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 dynamic temperature pressure group for measuring Supersonic Two Dimensional Unsteady flow field in the present embodiment
Probe, including end of probe (1), pole (2) are closed, end of probe (1) is wedge column structure, and circumscribed circle diameter is 6 millimeters, is visited
Needle section (1) is high 30 millimeters, and its inside is equipped with 3 dynamic pressure transducers, 1 dynamic temperature sensor, top surface (3) and probe
Pole (2) rotation axis is vertical, and end of probe (1) windward side is wedge during measurement, including symmetrical left surface (4) and right flank
(5), lee face is cylinder cambered surface (6)；In the leading edge that end of probe (1) left surface (4), right flank (5) and two sides have a common boundary
On be respectively provided with 1 pressure experience hole, respectively left hole (7), right hole (8), mesopore (9), this 3 not connected pressure experiences
Hole, connects with 3 dynamic pressure transducers in probe respectively；Dynamic temperature sensor head (10) exposes the milli of top surface (3) 2
Rice.
Probe pole (2) is cylinder, and 8 millimeters of diameter is provided with round passage, 5 millimeters of diameter inside it.
In costa, dynamic temperature sensor head (10) that end of probe (1) left surface (4) have a common boundary with right flank (5)
In approximately the same plane, left surface (4), right flank (5) are along the plane symmetry, left hole (7) and the right side for heart line, mesopore (9) center line
Hole (8) is distributed along the plane symmetry.End of probe (1) left surface (4), right flank (5) angle are 40 °
Mesopore (9) center of circle is 2 millimeters with the distance of end of probe (1) top surface (3).Left hole (10) center of circle and left surface (4),
The distance of the costa that right flank (5) has a common boundary is 3 millimeters, before right hole (11) center of circle has a common boundary with left surface (4), right flank (5)
The distance of edge line is 3 millimeters.Left hole (7), right hole (8), mesopore (9) the center of circle in approximately the same plane, a diameter of 0.6 millimeter.
The cable (11) of dynamic pressure transducer and dynamic temperature sensor through probe pole (2) internal channel, by probe tail
Draw in portion.
The dynamic temperature force combination probe in the measurement Supersonic Two Dimensional Unsteady flow field introduced in the embodiment of the present invention, passes through
Supersonic speed calibration wind tunnel is demarcated, and can obtain nominal data.During actual measurement supersonic speed Two Dimensional Unsteady flow field, the dynamic temperature
3 dynamic pressure transducers of force combination probe, 1 dynamic temperature sensor measure the unsteady pressure each experienced simultaneously
Power, unsteady temperature data, using the supersonic speed calibration wind tunnel nominal data for obtaining, carry out data processing, can obtain Supersonic
Temperature of incoming flow, stagnation pressure, static pressure, deflection angle, Mach number and two-dimension speed change with time.
Claims (8)
1. a kind of dynamic temperature force combination probe for measuring Supersonic Two Dimensional Unsteady flow field, it is characterised in that：Including probe
Portion (1), pole (2), the end of probe (1) is wedge column structure, and its inside is moved equipped with 3 dynamic pressure transducers, 1
State temperature sensor, top surface (3) is vertical with probe pole (2) rotation axis, and end of probe (1) windward side is wedge during measurement,
Including symmetrical left surface (4) and right flank (5), lee face is cylinder cambered surface (6)；On end of probe (1) left surface (4), the right side
1 pressure experience hole, respectively left hole (7), right hole (8), mesopore are respectively provided with the leading edge of side (5) and two sides boundary
(9), this 3 not connected pressure experience holes, connect with 3 dynamic pressure transducers in probe respectively；Dynamic temperature is passed
Sensor head (10) exposes top surface (3).
2. a kind of dynamic temperature force combination probe for measuring Supersonic Two Dimensional Unsteady flow field according to claim 1, its
It is characterised by：Probe pole (2) is column structure, can be cylinder, or triangular prism, is provided with inside it circular logical
Road.
3. a kind of dynamic temperature force combination probe for measuring Supersonic Two Dimensional Unsteady flow field according to claim 1, its
It is characterised by：Dynamic temperature sensor head (10) exposes (3) 1 millimeters to 5 millimeters of top surface.
4. a kind of dynamic temperature force combination probe for measuring Supersonic Two Dimensional Unsteady flow field according to claim 1, its
It is characterised by：End of probe (1) left surface (4), right flank (5) angle are 30 ° to 60 °.
5. a kind of dynamic temperature force combination probe for measuring Supersonic Two Dimensional Unsteady flow field according to claim 1, its
It is characterised by：In costa, dynamic temperature sensor head (10) that end of probe (1) left surface (4) have a common boundary with right flank (5)
In approximately the same plane, left surface (4), right flank (5) are along the plane symmetry, left hole (7) and the right side for heart line, mesopore (9) center line
Hole (8) is distributed along the plane symmetry.
6. a kind of dynamic temperature force combination probe for measuring Supersonic Two Dimensional Unsteady flow field according to claim 1, its
It is characterised by：Mesopore (9) center of circle is 1 millimeter to 5 millimeters with the distance of end of probe (1) top surface (3).
7. a kind of dynamic temperature force combination probe for measuring Supersonic Two Dimensional Unsteady flow field according to claim 1, its
It is characterised by：Left hole (7), right hole (8), a diameter of 0.6 millimeter to 1.5 millimeters of mesopore (9).
8. a kind of dynamic temperature force combination probe for measuring Supersonic Two Dimensional Unsteady flow field according to claim 1, its
It is characterised by：The cable (11) of dynamic pressure transducer and dynamic temperature sensor through probe pole (2) internal channel, by probe tail
Draw in portion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710126813.9A CN106768826B (en) | 2017-03-06 | 2017-03-06 | Dynamic temperature and pressure combined probe for measuring ultrasonic two-dimensional unsteady flow field |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710126813.9A CN106768826B (en) | 2017-03-06 | 2017-03-06 | Dynamic temperature and pressure combined probe for measuring ultrasonic two-dimensional unsteady flow field |
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| Publication Number | Publication Date |
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| CN106768826A true CN106768826A (en) | 2017-05-31 |
| CN106768826B CN106768826B (en) | 2020-02-21 |
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| CN201710126813.9A Active CN106768826B (en) | 2017-03-06 | 2017-03-06 | Dynamic temperature and pressure combined probe for measuring ultrasonic two-dimensional unsteady flow field |
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Cited By (2)
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| CN108195510A (en) * | 2018-01-23 | 2018-06-22 | 中国航空工业集团公司北京长城计量测试技术研究所 | A kind of hot air wind tunnel calibration method of hot diaphragm type shear stress sensor |
| CN112985751A (en) * | 2021-02-01 | 2021-06-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic wind tunnel stable section total temperature and total pressure test bent frame structure and manufacturing method |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108195510A (en) * | 2018-01-23 | 2018-06-22 | 中国航空工业集团公司北京长城计量测试技术研究所 | A kind of hot air wind tunnel calibration method of hot diaphragm type shear stress sensor |
| CN112985751A (en) * | 2021-02-01 | 2021-06-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic wind tunnel stable section total temperature and total pressure test bent frame structure and manufacturing method |
| CN112985751B (en) * | 2021-02-01 | 2022-09-23 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic wind tunnel stable section total temperature and total pressure test bent frame structure and manufacturing method |
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| CN106768826B (en) | 2020-02-21 |
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