CN106871968A - One kind measurement subsonic speed flow field multiple spot stagnation temperature stagnation pressure octal probe - Google Patents

One kind measurement subsonic speed flow field multiple spot stagnation temperature stagnation pressure octal probe Download PDF

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Publication number
CN106871968A
CN106871968A CN201710201090.4A CN201710201090A CN106871968A CN 106871968 A CN106871968 A CN 106871968A CN 201710201090 A CN201710201090 A CN 201710201090A CN 106871968 A CN106871968 A CN 106871968A
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CN
China
Prior art keywords
probe
hole
pressure
temperature
pressure experience
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CN201710201090.4A
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Chinese (zh)
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CN106871968B (en
Inventor
马宏伟
姜逸轩
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北京航空航天大学
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Priority to CN201710201090.4A priority Critical patent/CN106871968B/en
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Publication of CN106871968A publication Critical patent/CN106871968A/en
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Publication of CN106871968B publication Critical patent/CN106871968B/en

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    • GPHYSICS
    • G01MEASURING; TESTING
    • G01DMEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
    • G01D21/00Measuring or testing not otherwise provided for
    • G01D21/02Measuring two or more variables by means not covered by a single other subclass

Abstract

The invention belongs to turbine experimental test technical field, disclose a kind of measurement subsonic speed flow field multiple spot stagnation temperature stagnation pressure octal probe, including probe pole 1, end of probe 2, changeover portion 3, pressure guiding pipe 4 and temperature sensor cable 5, described probe pole 1, end of probe 2 is cylinder, end of probe 2 is connected on probe pole 1 by changeover portion 3, the face of cylinder front end of the end of probe 2 is provided with eight and experiences hole, including five pressure experience holes and three temperature sensation holes, five pressure guiding pipes of the five described pressure experience holes respectively with encapsulation in end of probe 2 are connected, three temperature sensation holes connect with temperature sensor respectively, pressure guiding pipe and temperature sensor cable draw probe tails by the internal channel of probe pole 1.Compared with existing probe, the present invention is demarcated by calibration, can simultaneously measure the flow velocity of location point, a flow direction in flow field, and multiple location points stagnation temperature, stagnation pressure, it is adaptable to the flow-field test between import and export and level such as subsonic fan, compressor, pump, blower fan.

Description

One kind measurement subsonic speed flow field multiple spot stagnation temperature stagnation pressure octal probe

Technical field

The invention belongs to turbomachine experimental test field, it is related to a kind of measurement subsonic speed flow field multiple spot stagnation temperature stagnation pressure octal Probe, the present invention can carry out the measurement of multiple spot stagnation temperature stagnation pressure in subsonic speed flow field, can realize accurate measurement.

Background technology

At present, in turbomachine field, especially aero-engine flow-field test field, the measurement of pressure and temperature is extensive Use pressure probe and temperature probe.The measurement of stagnation pressure, static pressure, Mach number, flow direction can be carried out using pressure probe.Pressure Force probe can not carry out temperature survey, therefore the data that cannot be measured by pressure probe are calculated the flow velocity in flow field.At present Measurement temperature of incoming flow generally uses single stagnation temperature probe, the stagnation temperature that stagnation temperature probe can measure to flow.

In existing probe test technology, for the flow field for needing measurement temperature and pressure simultaneously, existing probe test Means can only be measured using pressure probe and temperature probe respectively.This method complex operation, high cost, and may Bring extra error.The present invention proposes a kind of subsonic speed flow field multiple spot stagnation temperature stagnation pressure octal probe, uses single probe The measurement of pressure and temperature is carried out simultaneously, can simultaneously measure stagnation temperature, stagnation pressure, flow velocity, the flowing side of multiple location points in flow field To grade flow parameter.Calibrated demarcation is capable of achieving accurate measurement, in can apply to turbomachine experimental test.

The content of the invention

The present invention solves the technical problem of:For in current turbine experimental test, temperature probe and pressure are visited Pin is always separately used alone, test period is long, high cost, complex operation the problems such as, the present invention proposes a kind of subcritical flow Field multiple spot stagnation temperature stagnation pressure octal probe, the measurement of pressure and temperature can be simultaneously carried out using single probe, can be measured simultaneously The flow parameter such as stagnation temperature, stagnation pressure, flow velocity, flow direction of multiple location points in flow field.

In order to solve the above technical problems, the technical solution adopted by the present invention is:

One kind measurement subsonic speed flow field multiple spot stagnation temperature stagnation pressure octal probe, it is characterized in that, the probe includes probe pole (1), end of probe (2), changeover portion (3), pressure guiding pipe (4) and temperature sensor cable (5), the probe pole (1), probe Portion (2) is cylinder, and end of probe (2) is connected on probe pole (1) by changeover portion (3);The cylinder of end of probe (2) End is provided with eight and experiences hole, respectively pressure experience hole 1 (6), temperature sensation hole 1 (7), pressure experience hole 2 (8), pressure in front Experience hole 3 (9), pressure experience hole 4 (10), temperature sensation hole 2 (11), pressure experience hole 5 (12) and temperature sensation hole 3 (13), Eight are experienced center line of the centerline hole parallel and perpendicular to end of probe (2) cylinder;Five pressure experience holes respectively with probe Five pressure guiding pipes connection of encapsulation in head (2), three temperature sensation holes connect with temperature sensor respectively, pressure guiding pipe (4) and Temperature sensor cable (5) draws probe tails by probe pole (1) internal channel.

Further, pressure experience hole 1 (6) and pressure experience hole 5 (12) are circular port, and size is identical;Temperature sensation Hole 1 (7), temperature sensation hole 2 (11) and temperature sensation hole 3 (13) are identical, are circular port, and size is identical, is respectively equipped with hole One temperature sensor;Pressure experience hole 2 (8), pressure experience hole 3 (9) and pressure experience hole 4 (10) are mutually different impression Hole is in the center of circle in three holes is generally aligned in the same plane and parallel with cylinder bottom surface.

Further, pressure experience hole 2 (8), pressure experience hole 4 (10) are along the center line of pressure experience hole 3 (9) and cylinder center Plane symmetry distribution where line, diameter is identical, is 0.2~2 millimeter, pressure experience hole 2 (8) and pressure experience hole 4 (10) Centerlines are 60 °~100 °.

Further, geometry, size all phases in temperature sensation hole 1 (7), temperature sensation hole 2 (11) and temperature sensation hole 3 (13) Together, a diameter of 0.5~3 millimeter, pressure experience hole 1 (6) and temperature sensation hole 1 (7), pressure experience hole 5 (12) and temperature sensation The distance between center of hole 3 (13) is 1.1 times of bore dia~2 times bore dias.

Further, probe pole (1) is cylindrical structural, to play and be provided with passage inside supporting role, probe pole (1), Pressure guiding pipe (4) and temperature sensor cable (5) draw probe tails by probe pole (1) internal channel.

Further, temperature sensor can be thermocouple, or thermal resistance.

The beneficial effects of the invention are as follows:

Subsonic speed flow field multiple spot stagnation temperature stagnation pressure octal probe of the invention, can by single probe simultaneously carry out stagnation temperature, The measurement of stagnation pressure, flow velocity and flow direction;The flow field parameter of multiple location points can be obtained using single probe, can be truly The mobility status of the multiple location points of reflection;The use number of probe can be reduced, such that it is able to weaken number of probes excessively to stream The interference that field is brought;Probe uses the reduction of number simultaneously, it is also possible to reduces the cost of experimental test, reduce answering for experiment test Miscellaneous degree so that test operation is more easy to carry out during experimental test.

Brief description of the drawings

Fig. 1 is subsonic speed flow field multiple spot stagnation temperature stagnation pressure octal probe schematic diagram of the invention.

Fig. 2 is the top view of Fig. 1.

Wherein:1- probe poles, 2- end of probes, 3- changeover portions, 4- pressure guiding pipes, 5- temperature sensor cables, 6- pressure Experience hole 1,7- temperature sensations hole 1,8- pressure experiences hole 2,9- pressure experiences hole 3,10- pressure experiences hole 4,11- temperature sensations Hole 2,12- pressure experiences hole 5,13- temperature sensations hole 3.

Specific embodiment

Below by embodiment, subsonic speed flow field multiple spot stagnation temperature stagnation pressure octal probe of the invention is carried out in detail with reference to accompanying drawing It is thin to illustrate, so that the features and advantages of the present invention can be easier to be understood by the person skilled in the art such that it is able to this hair Bright protection domain is made and becomes apparent from clearly defining.

As shown in Figure 1, a kind of subsonic speed flow field multiple spot stagnation temperature stagnation pressure octal probe is described in the present embodiment, including is visited Pin pole (1), end of probe (2), changeover portion (3), pressure guiding pipe (4) and temperature sensor cable (5), described probe pole (1), end of probe (2) is cylinder, and end of probe (2) is connected on probe pole (1) by changeover portion (3), the spy The face of cylinder front end of needle section (2) is provided with eight and experiences hole, including five pressure experience holes and three temperature sensation holes, described Five pressure guiding pipes of five pressure experience holes respectively with encapsulation in end of probe (2) are connected, three temperature sensation holes respectively with temperature Degree sensor connection, pressure guiding pipe and temperature sensor cable draw probe tails by probe pole (1) internal channel.Five pressure Experience in hole, pressure experience hole 1 (6), pressure experience hole 3 (9) and pore pressure force impression 5 (12) is total pressure measurement hole, can be measured To flow stagnation pressure, pressure experience hole 2 (8), pressure experience hole 3 (9) and pressure experience hole 4 (10) combine and can measure two-dimensional flow The Mach number of field and flow direction.Five pressure experience holes connect with five pressure guiding pipes encapsulated in end of probe respectively.Three Temperature sensation hole can carry out the measurement of multiple spot stagnation temperature built with temperature sensor.Pressure guiding pipe and temperature sensor cable pass through Probe pole internal channel draws probe tails.

As shown in Figure 1, subsonic speed flow field multiple spot stagnation temperature stagnation pressure octal probe of the invention is probeed into tested flow field, is pressed Power experiences hole 3 (9) towards direction of flow, and probe pole central axis are in direction of flow.End of probe pressure experience hole 1 (6), What pressure experience hole 3 (9) and pressure experience hole 5 (12) can measure multiple location points flows stagnation pressure, pressure experience hole 2 (8), pressure Power experiences hole 3 (9), pressure experience hole 4 (10) can measure free stream Mach number and flow direction.Temperature sensation hole 1 (7), temperature Experiencing hole 2 (11) and temperature sensation hole 3 (13) can measure the stagnation temperature of multiple location points.

Claims (6)

1. the present invention is a kind of measurement subsonic speed flow field multiple spot stagnation temperature stagnation pressure octal probe, it is characterized in that, the probe includes visiting Pin pole (1), end of probe (2), changeover portion (3), pressure guiding pipe (4) and temperature sensor cable (5), the probe pole (1), End of probe (2) is cylinder, and end of probe (2) is connected on probe pole (1) by changeover portion (3);End of probe (2) Face of cylinder front end be provided with eight and experience hole, respectively pressure experience hole 1 (6), temperature sensation hole 1 (7), pressure experience hole 2 (8), pressure experience hole 3 (9), pressure experience hole 4 (10), temperature sensation hole 2 (11), pressure experience hole 5 (12) and temperature sensation Hole 3 (13), eight are experienced center line of the centerline hole parallel and perpendicular to end of probe (2) cylinder;Five pressure experience holes point Five pressure guiding pipes not with encapsulation in end of probe (2) are connected, and three temperature sensation holes connect with temperature sensor respectively, impulse Pipe (4) and temperature sensor cable (5) draw probe tails by probe pole (1) internal channel.
2., according to the requirement of right 1, pressure experience hole 1 (6) and pressure experience hole 5 (12) are circular port, and size is identical;Temperature It is identical that degree experiences hole 1 (7), temperature sensation hole 2 (11) and temperature sensation hole 3 (13), is circular port, and size is identical, in hole One temperature sensor is respectively housed;Pressure experience hole 2 (8), pressure experience hole 3 (9) and pressure experience hole 4 (10) are different Impression hole, it is in the center of circle in three holes is generally aligned in the same plane and parallel with cylinder bottom surface.
3. according to the requirement of right 1, pressure experience hole 2 (8), pressure experience hole 4 (10) along the center line of pressure experience hole 3 (9) and Plane symmetry distribution where cylinder center line, diameter is identical, is 0.2~2 millimeter, pressure experience hole 2 (8) and pressure experience The centerlines of hole 4 (10) are 60 °~100 °.
4. according to the requirement of right 1, temperature sensation hole 1 (7), the geometry in temperature sensation hole 2 (11) and temperature sensation hole 3 (13), All be the same size, a diameter of 0.5~3 millimeter, pressure experience hole 1 (6) and temperature sensation hole 1 (7), pressure experience hole 5 (12) with The distance between center of temperature sensation hole 3 (13) is 1.1 times of bore dia~2 times bore dias.
5. according to the requirement of right 1, probe pole (1) is cylindrical structural, plays and is opened inside supporting role, probe pole (1) There is passage, pressure guiding pipe (4) and temperature sensor cable (5) draw probe tails by probe pole (1) internal channel.
6., according to the requirement of right 1, temperature sensor can be thermocouple, or thermal resistance.
CN201710201090.4A 2017-03-30 Probe for measuring total pressure of total temperature of multiple points of subsonic flow field CN106871968B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201710201090.4A CN106871968B (en) 2017-03-30 Probe for measuring total pressure of total temperature of multiple points of subsonic flow field

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201710201090.4A CN106871968B (en) 2017-03-30 Probe for measuring total pressure of total temperature of multiple points of subsonic flow field

Publications (2)

Publication Number Publication Date
CN106871968A true CN106871968A (en) 2017-06-20
CN106871968B CN106871968B (en) 2020-07-03

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Cited By (1)

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CN107907232A (en) * 2017-12-21 2018-04-13 沈阳鼓风机集团股份有限公司 For measuring the temperature pressure combinations probe of turbomachinery interior flow field

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WO1994020014A1 (en) * 1993-03-05 1994-09-15 Sahagen Armen N Probe for monitoring a fluid medium
DE4337402A1 (en) * 1993-10-26 1995-04-27 Mannesmann Ag Probe for measuring pressure and temperature profiles
CN104048808A (en) * 2013-03-14 2014-09-17 中国科学院工程热物理研究所 Dynamic entropy probe
CN103884467A (en) * 2014-04-14 2014-06-25 中国科学院工程热物理研究所 Plasma pressure probe and system for measuring pressure by utilizing plasma pressure probe
CN106404409A (en) * 2016-11-16 2017-02-15 中国科学院工程热物理研究所 Probe assembly suitable for strong-shearing unsteady flow test of aeroengine

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107907232A (en) * 2017-12-21 2018-04-13 沈阳鼓风机集团股份有限公司 For measuring the temperature pressure combinations probe of turbomachinery interior flow field

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