CN106768826B - Dynamic temperature and pressure combined probe for measuring ultrasonic two-dimensional unsteady flow field - Google Patents
Dynamic temperature and pressure combined probe for measuring ultrasonic two-dimensional unsteady flow field Download PDFInfo
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- CN106768826B CN106768826B CN201710126813.9A CN201710126813A CN106768826B CN 106768826 B CN106768826 B CN 106768826B CN 201710126813 A CN201710126813 A CN 201710126813A CN 106768826 B CN106768826 B CN 106768826B
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention belongs to the technical field of temperature and pressure tests, and discloses a dynamic temperature and pressure combined probe for measuring an ultrasonic two-dimensional unsteady flow field, which comprises a probe head part and a support rod, wherein the probe head part is of a wedge-shaped columnar structure, and 3 dynamic pressure sensors and 1 dynamic temperature sensor are arranged in the probe head part. During measurement, the windward side of the head of the probe comprises a left side surface and a right side surface, and the leeward side surface is a cylindrical cambered surface. The front edges of the left side surface, the right side surface and the junction of the two side surfaces are respectively provided with 1 pressure sensing hole which is respectively communicated with 3 dynamic pressure sensors in the head part of the probe, the head part of the dynamic temperature sensor is exposed out of the top surface of the head part of the probe, and a sensor cable is led out of the tail part of the probe through a channel in the supporting rod. Compared with the existing pressure probe, the ultrasonic two-dimensional unsteady flow field parameter measuring device can measure the change of ultrasonic incoming flow temperature, total pressure, static pressure, deflection angle, Mach number and two-dimensional speed along with time at the same time through calibration of the wind tunnel, and provides a means for efficiently, accurately and comprehensively measuring ultrasonic two-dimensional unsteady flow field parameters for a turbine experiment.
Description
Technical Field
The invention belongs to the technical field of temperature and pressure tests, relates to a dynamic temperature and dynamic pressure measuring device of a supersonic two-dimensional unsteady flow field, and particularly relates to a dynamic temperature and pressure combined probe for measuring an ultrasonic two-dimensional unsteady flow field, which is suitable for testing supersonic speed two-dimensional dynamic flow fields of an aircraft engine supersonic speed air inlet, an impeller mechanical inlet, an outlet and an interstage.
Background
The existence of hot spots in the incoming flow of turbine inlets of aircraft engines and gas turbines can affect the distribution of downstream temperature fields and even seriously affect the thermal load and the service life of turbine blades. The research on the propagation mechanism of the hot spot in the turbine guider and between stages needs to measure the unsteady velocity field, the pressure field and the temperature field of the supersonic two-dimensional flow field at the outlet of the turbine guider.
At present, three-hole pressure probes and total temperature probes are generally adopted respectively, and the probes are driven to go to a measured position by a displacement mechanism arranged on a casing to measure. The three-hole pressure probe can only provide total pressure, static pressure, deflection angle and Mach number of incoming flow, and the total temperature probe can only provide total temperature data.
The experimental research carried out by using the existing probe measurement technology has the following problems: 1. the two probes are used for measurement respectively, so that the test time is long and the test cost is high; 2. the two probes are used for measurement respectively, the probes need to be replaced in the test process, the incoming flow working conditions have certain changes, and particularly the temperature fields are inconsistent; 3. the measuring point positions of different probes are influenced by the positioning of the displacement mechanism possibly differently, the flow parameter data measured by different probes are certainly not from the same streamline, and when the flow parameter data measured by the probes are combined to calculate parameters such as speed and the like, data errors are brought, so that the total measuring result is brought with non-negligible errors; 4. due to the rotation of the turbine rotor blades, the supersonic two-dimensional flow field at the outlet of the turbine guide vane is abnormal, changes along with the change of the positions of the rotor blade blades, and the existing probe technology can only provide steady-state pressure, temperature and speed data and cannot reflect the abnormal propagation mechanism of the hot spot in the turbine.
Disclosure of Invention
The invention aims to solve the problem that the existing probe technology cannot simultaneously provide data of dynamic pressure, dynamic temperature and dynamic speed of a measured flow field in a turbine supersonic two-dimensional dynamic flow field propagation test of hot spots.
The technical solution of the invention is as follows:
1. the utility model provides a measure dynamic temperature pressure combination probe of super sound two-dimensional unsteady flow field which characterized in that: the probe comprises a probe head (1) and a supporting rod (2), wherein the probe head (1) is of a wedge-shaped columnar structure, 3 dynamic pressure sensors and 1 dynamic temperature sensor are arranged in the probe head, a top surface (3) is perpendicular to a rotation axis of the probe supporting rod (2), the windward side of the probe head (1) is a wedge during measurement and comprises a left side surface (4) and a right side surface (5) which are symmetrical, and the leeward side is a cylindrical cambered surface (6); 1 pressure sensing holes, namely a left hole (7), a right hole (8) and a middle hole (9), are respectively formed in the front edges of the left side surface (4), the right side surface (5) and the junction of the two side surfaces of the probe head (1), and the 3 pressure sensing holes which are not communicated with each other are respectively communicated with 3 dynamic pressure sensors in the probe; the dynamic temperature sensor head (10) is exposed at the top surface (3).
2. Furthermore, the probe supporting rod (2) is of a columnar structure, can be a cylinder or a triangular prism, and is internally provided with a circular channel.
3. Further, the dynamic temperature sensor head (10) is exposed to the top surface (3) by 1 mm to 5 mm.
4. Furthermore, the included angle of the left side surface (4) and the right side surface (5) of the probe head (1) is 30-60 degrees.
5. Furthermore, a front edge line of a junction of the left side surface (4) and the right side surface (5) of the probe head (1), a central line of the dynamic temperature sensor head (10) and a central line of the middle hole (9) are on the same plane, the left side surface (4) and the right side surface (5) are symmetrical along the plane, and the left hole (7) and the right hole (8) are symmetrically distributed along the plane.
6. Furthermore, the distance between the center of the middle hole (9) and the top surface (3) of the probe head (1) is 1 mm to 5 mm.
7. Further, the diameters of the left hole (7), the right hole (8) and the middle hole (9) are 0.6 mm to 1.5 mm.
8. Furthermore, cables (11) of the dynamic pressure sensor and the dynamic temperature sensor are led out from the tail of the probe through a channel in the probe supporting rod (2).
The invention has the beneficial effects that:
compared with the existing pressure probe, the ultrasonic two-dimensional unsteady flow field parameter measuring device can measure the change of ultrasonic incoming flow temperature, total pressure, static pressure, deflection angle, Mach number and two-dimensional speed along with time at the same time through calibration of the wind tunnel, and provides a means for efficiently, accurately and comprehensively measuring ultrasonic two-dimensional unsteady flow field parameters for a turbine experiment.
Drawings
Fig. 1 is a schematic structural diagram of a dynamic temperature and pressure combination probe for measuring an ultrasonic two-dimensional unsteady flow field in an embodiment of the present invention.
Fig. 2 is a left side view of fig. 1.
Fig. 3 is a top view of fig. 1.
Wherein: 1-probe head, 2-probe support rod, 3-top surface, 4-left side surface, 5-right side surface, 6-cylindrical cambered surface, 7-left hole, 8-right hole, 9-middle hole, 10-dynamic temperature sensor head and 11-cable.
Detailed Description
The invention is described in detail below with reference to the figures and specific embodiments.
As shown in fig. 1, the embodiment of the invention provides a dynamic temperature and pressure combined probe for measuring an ultrasonic two-dimensional unsteady flow field, which comprises a probe head (1) and a support rod (2), wherein the probe head (1) is of a wedge-shaped columnar structure, the diameter of an external circle is 6 mm, the height of the probe head (1) is 30 mm, 3 dynamic pressure sensors and 1 dynamic temperature sensor are arranged in the probe head, the top surface (3) is perpendicular to the rotation axis of the probe support rod (2), the windward surface of the probe head (1) is a wedge during measurement, the probe head comprises a left side surface (4) and a right side surface (5) which are symmetrical, and the leeward surface is a cylindrical cambered surface (6); 1 pressure sensing holes, namely a left hole (7), a right hole (8) and a middle hole (9), are respectively formed in the front edges of the left side surface (4), the right side surface (5) and the junction of the two side surfaces of the probe head (1), and the 3 pressure sensing holes which are not communicated with each other are respectively communicated with 3 dynamic pressure sensors in the probe; the dynamic temperature sensor head (10) is exposed to the top surface (3) by 2 mm.
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 front edge line of the junction of the left side surface (4) and the right side surface (5) of the probe head (1), the central line of the dynamic temperature sensor head (10) and the central line of the middle hole (9) are on the same plane, the left side surface (4) and the right side surface (5) are symmetrical along the plane, and the left hole (7) and the right hole (8) are symmetrically distributed along the plane. The included angle of the left side surface (4) and the right side surface (5) of the probe head (1) is 40 DEG
The distance between the center of the center hole (9) and the top surface (3) of the probe head (1) is 2 mm. The distance between the circle center of the left hole (10) and the front edge line of the junction of the left side surface (4) and the right side surface (5) is 3 mm, and the distance between the circle center of the right hole (11) and the front edge line of the junction of the left side surface (4) and the right side surface (5) is 3 mm. The circle centers of the left hole (7), the right hole (8) and the middle hole (9) are on the same plane, and the diameter is 0.6 mm.
Cables (11) of the dynamic pressure sensor and the dynamic temperature sensor are led out from the tail part of the probe through a channel in the probe supporting rod (2).
The dynamic temperature and pressure combined probe for measuring the ultrasonic two-dimensional unsteady flow field disclosed in the embodiment of the invention can obtain calibration data through supersonic calibration wind tunnel calibration. When the supersonic two-dimensional unsteady flow field is actually measured, the 3 dynamic pressure sensors and the 1 dynamic temperature sensor of the dynamic temperature and pressure combined probe simultaneously measure unsteady pressure and unsteady temperature data respectively sensed, and the obtained supersonic calibration wind tunnel calibration data is utilized to carry out data processing, so that the change of supersonic incoming flow temperature, total pressure, static pressure, deflection angle, Mach number and two-dimensional speed along with time can be obtained.
Claims (1)
1. The utility model provides a measure dynamic temperature pressure combination probe of super sound two-dimensional unsteady flow field which characterized in that: the probe comprises a probe head (1) and a supporting rod (2), wherein the probe head (1) is of a wedge-shaped columnar structure, 3 dynamic pressure sensors and one dynamic temperature sensor are arranged in the probe head, a top surface (3) is perpendicular to a rotation axis of the probe supporting rod (2), the windward side of the probe head (1) is a wedge during measurement and comprises a left side surface (4) and a right side surface (5) which are symmetrical, and the leeward side is a cylindrical cambered surface (6); 1 pressure sensing holes, namely a left hole (7), a right hole (8) and a middle hole (9), are respectively formed in the front edges of the left side surface (4), the right side surface (5) and the junction of the two side surfaces of the probe head (1), and the 3 pressure sensing holes which are not communicated with each other are respectively communicated with 3 dynamic pressure sensors in the probe; the dynamic temperature sensor head (10) is exposed out of the top surface (3);
the probe supporting rod (2) is of a columnar structure, can be a cylinder or a triangular prism, and is internally provided with a circular channel;
the dynamic temperature sensor head (10) is exposed out of the top surface (3) by 1 mm to 5 mm;
the included angle of the left side surface (4) and the right side surface (5) of the probe head (1) is 30-60 degrees;
the front edge line of the junction of the left side surface (4) and the right side surface (5) of the probe head (1), the central line of the dynamic temperature sensor head (10) and the central line of the middle hole (9) are on the same plane, the left side surface (4) and the right side surface (5) are symmetrical along the plane, and the left hole (7) and the right hole (8) are symmetrically distributed along the plane;
the distance between the center of the middle hole (9) and the top surface (3) of the probe head (1) is 1-5 mm;
the diameters of the left hole (7), the right hole (8) and the middle hole (9) are 0.6 mm to 1.5 mm;
the cables (11) of the dynamic pressure sensor and the dynamic temperature sensor are led out from the tail part of the probe through the inner channel of the probe supporting rod (2),
the combined probe can simultaneously measure the change of ultrasonic incoming flow temperature, total pressure, static pressure, deflection angle, Mach number and two-dimensional speed along with time.
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 |
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| Application Number | Priority Date | Filing Date | Title |
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| 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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| CN106768826A CN106768826A (en) | 2017-05-31 |
| CN106768826B true CN106768826B (en) | 2020-02-21 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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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 |
| 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 |
| CN115436656B (en) * | 2022-09-06 | 2024-05-21 | 北京航空航天大学 | Eight-shaped hot wire probe for measuring two-dimensional velocity field between stages of compressor |
Citations (4)
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| CN203083805U (en) * | 2013-01-24 | 2013-07-24 | 北京航空航天大学 | Near-wall hot-wire probe capable of measuring backflow |
| 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 |
| CN105716788A (en) * | 2015-11-02 | 2016-06-29 | 北京航空航天大学 | Three-hole transonic speed pressure probe |
| CN105716779A (en) * | 2015-11-02 | 2016-06-29 | 北京航空航天大学 | Dynamic pressure blade type probe |
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2017
- 2017-03-06 CN CN201710126813.9A patent/CN106768826B/en active Active
Patent Citations (4)
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|---|---|---|---|---|
| CN203083805U (en) * | 2013-01-24 | 2013-07-24 | 北京航空航天大学 | Near-wall hot-wire probe capable of measuring backflow |
| 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 |
| CN105716788A (en) * | 2015-11-02 | 2016-06-29 | 北京航空航天大学 | Three-hole transonic speed pressure probe |
| CN105716779A (en) * | 2015-11-02 | 2016-06-29 | 北京航空航天大学 | Dynamic pressure blade type probe |
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| "一种测量跨声速多级压气机转子出口二维流场的方法";马宏伟 等;《推进技术》;20130726;第34卷(第6期);第754-759页 * |
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