CN106940241B - Steady-state temperature and pressure combined probe for measuring transonic three-dimensional flow field - Google Patents
Steady-state temperature and pressure combined probe for measuring transonic three-dimensional flow field Download PDFInfo
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- CN106940241B CN106940241B CN201710122006.XA CN201710122006A CN106940241B CN 106940241 B CN106940241 B CN 106940241B CN 201710122006 A CN201710122006 A CN 201710122006A CN 106940241 B CN106940241 B CN 106940241B
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- 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
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Abstract
The invention belongs to the technical field of temperature and pressure testing, and discloses a steady-state temperature and pressure combined probe for measuring a transonic three-dimensional flow field, which comprises a probe head and a support rod, wherein the probe head is of a wedge-top prismatic structure, the windward side of the probe head comprises a wedge-top inclined plane, a front plane, a left side plane and a right side plane, the leeward side of the probe head is a prismatic side plane, 4 pressure sensing holes and 1 temperature sensing hole are formed in the windward side of the probe head, the 4 pressure sensing holes are respectively communicated with 4 pressure leading pipes packaged in the probe head, the temperature sensing holes are only communicated with a temperature sensor packaged in the temperature sensing holes, and the pressure leading pipes and a temperature sensor cable lead out of the tail of the probe through an inner channel of the probe support rod. Compared with the existing pressure probe, the method can simultaneously measure the steady-state temperature, total pressure, static pressure, deflection angle, pitch angle, Mach number and three-dimensional speed of transonic incoming flow through calibration of the wind tunnel, and provides a means for efficiently, accurately and comprehensively measuring transonic three-dimensional steady-state flow field parameters for a turbine experiment.
Description
Technical Field
The invention belongs to the technical field of flow field temperature and pressure testing, relates to a steady-state temperature and steady-state pressure measuring device of a transonic three-dimensional flow field, and particularly relates to a steady-state temperature and pressure combined probe for measuring the transonic three-dimensional flow field, which is suitable for testing transonic three-dimensional steady-state flow fields at an inlet, an outlet and an interstage of an impeller machine.
Background
At present, a five-hole pressure probe is generally adopted, and the five-hole pressure probe is driven to move to a measured position by a displacement mechanism arranged on a casing to measure the transonic speed three-dimensional steady-state flow field at an inlet, an outlet and an inter-stage of the transonic compressor. The five-hole pressure probe can only provide total pressure, static pressure, deflection angle, pitch angle and Mach number of incoming flow, and the incoming flow speed data cannot be calculated from the data measured by the five-hole pressure probe because the five-hole pressure probe cannot measure temperature data. The temperature is an important parameter for representing the thermodynamic property of incoming flow, an independent total temperature probe is required to be adopted for measuring the incoming flow temperature at present, and the total temperature probe is driven to move to a measured position by means of a displacement mechanism arranged on a casing to carry out independent measurement.
The existing probe measurement technology cannot simultaneously measure the flow parameters such as total temperature, total pressure, static pressure, deflection angle, pitch angle, Mach number and the like of airflow of the transonic compressor, on one hand, the measurement time is long, the test cost is high, importantly, the working condition of the incoming flow can have certain change, on the other hand, the measuring point positions of different probes can be possibly different under the influence of the positioning of a displacement mechanism, the flow parameter data measured by different probes are certainly not from the same streamline, when the probes are used for measuring data and the parameters such as speed and the like are combined and calculated, data errors can be brought, and further, the errors which are not negligible can be brought to the total measurement result.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the invention provides a steady-state temperature and pressure combined probe for measuring a transonic three-dimensional flow field, which can simultaneously measure the steady-state temperature, total pressure, static pressure, deflection angle, pitch angle, Mach number and three-dimensional speed of transonic incoming flow compared with the existing pressure probe and aims at solving the problems of long measuring time, high test cost, poor consistency of measuring working conditions and large measuring error caused by adopting different probes such as an independent total temperature probe, a five-hole pressure probe and the like in the existing transonic three-dimensional flow field measuring test of the transonic compressor.
The technical solution of the invention is as follows:
1. a steady state temperature and pressure combined probe for measuring transonic three-dimensional flow field is characterized in that: the probe comprises a probe head (1) and a support rod (2), wherein the probe head (1) is of a wedge-top prism structure, the windward side of the probe head (1) during probe measurement comprises a wedge-top inclined plane (3), a front plane (4), a symmetrical left side plane (5) and a right side plane (6), and the leeward side is a prism side plane (7); a pressure sensing hole is formed in a wedge top inclined plane (3) of the probe head (1) and is an upper hole (8), 1 pressure sensing hole is formed in each of a left plane (5), a right plane (6) and a front plane (4) of the probe head (1) and is a left hole (9), a right hole (10) and a middle hole (11), and the 4 pressure sensing holes which are not communicated with each other are respectively communicated with one end of 4 pressure guiding pipes (12) in the probe head (1); a temperature sensing hole (13) is arranged right below the middle hole (11), and a temperature sensor is arranged in the temperature sensing hole.
2. Further, the side edges of the wedge-top prism of the probe head (1) are parallel to the axis of the probe support rod (2).
3. Furthermore, the central line of an upper hole (8), the central line of a middle hole (11), the central line of a temperature sensing hole (13) and the axis of the probe supporting rod (2) of the probe head (1) are on the same plane, a left plane (5) and a right plane (6) are symmetrical along the plane, a left hole (9) and a right hole (10) are symmetrically distributed along the plane, and the included angle between the left plane (5) and the right plane (6) is 30-78 degrees.
4. Furthermore, the included angle between the wedge top inclined plane (3) of the probe head (1) and the axis of the probe support rod (2) is 32-55 degrees.
5. Furthermore, the distance between the circle center of the upper hole (8) of the probe head (1) and the bottom edge of the wedge top inclined plane is 1 mm to 5 mm.
6. Furthermore, the width of the front plane (4) of the probe head (1) is 1 mm to 2 mm, and the distance between the center of the middle hole (11) and the bottom edge of the wedge top inclined plane is 1 mm to 4 mm.
7. Furthermore, the temperature sensing hole (13) is positioned right below the middle hole (11), the diameter is 1 mm to 2 mm, and the distance between the temperature sensing hole (13) and the middle hole (11) is 1 mm to 3 mm.
8. Further, the diameters of the 4 pressure sensing holes of the probe head (1) are 0.2 mm to 1 mm.
9. Further, the wedge-top prism structure of the probe head (1) has a height of 15 mm to 50 mm and can be machined from a cylinder with a diameter of 4 mm to 8 mm.
10. Furthermore, the probe supporting rod (2) is a cylinder, a circular pipeline is arranged in the probe supporting rod, and 4 pressure leading pipes (12) and 4 temperature sensor cables (14) which are respectively communicated with the 4 pressure sensing holes are led out of the tail part of the probe through the pipeline in the probe supporting rod (2).
The invention has the beneficial effects that:
compared with the existing pressure probe, the method can simultaneously measure the steady-state temperature, total pressure, static pressure, deflection angle, pitch angle, Mach number and three-dimensional speed of transonic incoming flow through calibration of the wind tunnel, and provides a means for efficiently, accurately and comprehensively measuring transonic three-dimensional steady-state flow field parameters for a turbine experiment.
Drawings
Fig. 1 is a schematic structural diagram of a steady-state temperature and pressure combination probe for measuring a transonic three-dimensional flow field in an embodiment of the present invention.
Fig. 2 is a left side view of fig. 1.
Fig. 3 is a view from direction a of fig. 2.
Wherein: 1-probe head, 2-probe support rod, 3-wedge top inclined plane, 4-front plane, 5-left side plane, 6-right side plane, 7-prism side plane, 8-upper hole, 9-left hole, 10-right hole, 11-middle hole, 12-pressure leading pipe, 13-temperature sensing hole and 14-temperature sensor cable.
Detailed Description
The invention is described in detail below with reference to the figures and specific embodiments.
As shown in fig. 1, the present embodiment introduces a steady-state temperature and pressure combined probe for measuring a transonic three-dimensional flow field, including a probe head (1) and a support rod (2), where the probe head (1) is of a wedge-top prism structure, the diameter of an external circle is 6 mm, the height of the probe head (1) is 30 mm, a windward surface of the probe head (1) during probe measurement includes a wedge-top inclined plane (3), a front plane (4), a left plane (5) and a right plane (6) that are symmetrical, and a leeward surface is a prism-side plane (7); a pressure sensing hole is formed in a wedge top inclined plane (3) of the probe head (1) and is an upper hole (8), 1 pressure sensing hole is formed in each of a left plane (5), a right plane (6) and a front plane (4) of the probe head (1) and is a left hole (9), a right hole (10) and a middle hole (11), and the 4 pressure sensing holes which are not communicated with each other are respectively communicated with one end of 4 pressure guiding pipes (12) in the probe head (1); a temperature sensing hole (13) is arranged right below the middle hole (11), and a temperature sensor is arranged in the temperature sensing hole.
The probe supporting rod (2) is a cylinder with the diameter of 8 mm, and a circular channel with the diameter of 5 mm is arranged in the probe supporting rod.
The side edges of the wedge top prism of the probe head (1) are parallel to the axis of the probe support rod (2).
The central line of an upper hole (8), the central line of a middle hole (11), the central line of a temperature sensing hole (13) and the axis of a probe supporting rod (2) are on the same plane, a left plane (5) and a right plane (6) are symmetrical along the plane, a left hole (9) and a right hole (10) are symmetrically distributed along the plane, and the included angle between the left plane (5) and the right plane (6) is 40 degrees.
The included angle between the wedge top inclined plane (3) of the probe head (1) and the axis of the probe supporting rod (2) is 40 degrees.
The distance between the circle center of an upper hole (8) of the probe head (1) and the bottom edge of the wedge top inclined plane is 2 mm.
The front plane (4) of the probe head (1) is 1 mm wide, and the distance between the center of the middle hole (11) and the bottom edge of the wedge top inclined plane is 1 mm.
The temperature sensing hole (13) is positioned right below the middle hole (11), the diameter of the temperature sensing hole is 1 mm, and the distance between the temperature sensing hole (13) and the middle hole (11) is 1 mm.
The circle centers of the left hole (9), the right hole (10) and the middle hole (11) are on the same plane, the distance between the circle center of the left hole (9) and the left side of the front plane (4) is 3 mm, and the distance between the circle center of the right hole (10) and the right side of the front plane (4) is 3 mm.
The diameter of the 4 pressure sensing holes of the probe head (1) is 0.5 mm.
4 pressure leading pipes (12) respectively communicated with the 4 pressure sensing holes and a temperature sensor cable (14) are led out of the tail part of the probe through a pipeline in the probe supporting rod (2).
The steady-state temperature and pressure combined probe for measuring the transonic three-dimensional flow field disclosed in the embodiment of the invention can obtain calibration data through transonic calibration wind tunnel calibration. When a transonic three-dimensional flow field is actually measured, 4 pressure sensing holes of the steady-state temperature and pressure combination probe and 1 temperature sensor simultaneously measure steady-state pressure and temperature data respectively sensed, the obtained transonic calibration wind tunnel calibration data is utilized to carry out data processing, and transonic incoming flow steady-state temperature, total pressure, static pressure, deflection angle, pitch angle, Mach number and three-dimensional speed data can be obtained.
Claims (1)
1. A steady state temperature and pressure combined probe for measuring transonic three-dimensional flow field is characterized in that: the probe comprises a probe head (1) and a support rod (2), wherein the probe head (1) is of a wedge-top prism structure, the windward side of the probe head (1) during probe measurement comprises a wedge-top inclined plane (3), a front plane (4), a symmetrical left side plane (5) and a right side plane (6), and the leeward side is a prism side plane (7); a pressure sensing hole is formed in a wedge top inclined plane (3) of the probe head (1) and is an upper hole (8), 1 pressure sensing hole is formed in each of a left plane (5), a right plane (6) and a front plane (4) of the probe head (1) and is a left hole (9), a right hole (10) and a middle hole (11), and the 4 pressure sensing holes which are not communicated with each other are respectively communicated with one end of 4 pressure guiding pipes (12) in the probe head (1); a temperature sensing hole (13) is arranged right below the middle hole (11), and a temperature sensor is arranged in the temperature sensing hole;
the side edge of the wedge top prism of the probe head (1) is parallel to the axis of the probe support rod (2);
the central line of an upper hole (8), the central line of a middle hole (11), the central line of a temperature sensing hole (13) and the axis of the probe supporting rod (2) are on the same plane, a left plane (5) and a right plane (6) are symmetrical along the plane, a left hole (9) and a right hole (10) are symmetrically distributed along the plane, and the included angle between the left plane (5) and the right plane (6) is 30-78 degrees;
the included angle between the wedge top inclined plane (3) of the probe head (1) and the axis of the probe support rod (2) is 32-55 degrees;
the distance between the circle center of an upper hole (8) of the probe head (1) and the bottom edge of the wedge top inclined plane is 1 mm to 5 mm;
the width of a front plane (4) of the probe head (1) is 1 mm to 2 mm, and the distance between the center of the middle hole (11) and the bottom edge of the wedge top inclined plane is 1 mm to 4 mm;
the temperature sensing hole (13) is positioned right below the middle hole (11), the diameter is 1 mm to 2 mm, and the distance between the temperature sensing hole (13) and the middle hole (11) is 1 mm to 3 mm;
the diameters of 4 pressure sensing holes of the probe head (1) are 0.2 mm to 1 mm;
the wedge-top prism structure of the probe head (1) is 15-50 mm high and can be processed by a cylinder, and the diameter of the cylinder is 4-8 mm;
the probe supporting rod (2) is a cylinder, a circular pipeline is arranged in the probe supporting rod, 4 pressure leading pipes (12) which are respectively communicated with 4 pressure sensing holes and a temperature sensor cable (14) are led out of the tail part of the probe through the pipeline in the probe supporting rod (2);
the steady-state temperature and pressure combined probe for measuring the transonic three-dimensional flow field can simultaneously measure the steady-state temperature, the total pressure, the static pressure, the deflection angle, the pitch angle, the Mach number and the three-dimensional speed of transonic incoming flow.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710122006.XA CN106940241B (en) | 2017-03-03 | 2017-03-03 | Steady-state temperature and pressure combined probe for measuring transonic three-dimensional flow field |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710122006.XA CN106940241B (en) | 2017-03-03 | 2017-03-03 | Steady-state temperature and pressure combined probe for measuring transonic three-dimensional flow field |
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| CN106940241A CN106940241A (en) | 2017-07-11 |
| CN106940241B true CN106940241B (en) | 2020-02-21 |
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| CN110514390B (en) * | 2019-08-12 | 2020-12-04 | 北京航空航天大学 | Three-hole pressure probe measurement two-dimensional flow field uncertainty evaluation method |
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| FR2960596B1 (en) * | 2010-05-25 | 2014-05-02 | Turbomeca | DEVICE FOR THE MULTIPURPOSE ACQUISITION / DISTRIBUTION OF FLUID, IN PARTICULAR PRESSURE TAKING PROBE IN A TURBOMACHINE AIR INLET |
| CN202582868U (en) * | 2012-05-11 | 2012-12-05 | 西北工业大学 | Testing device for measuring wing type wake flow field |
| 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 |
| CN105716779B (en) * | 2015-11-02 | 2019-02-22 | 北京航空航天大学 | Dynamic pressure blade profile probe |
| CN105716788B (en) * | 2015-11-02 | 2019-02-22 | 北京航空航天大学 | Three hole transonic speed pressure probes |
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