CN106908191B - Dynamic temperature and pressure combined probe for measuring transonic two-dimensional unsteady flow field - Google Patents
Dynamic temperature and pressure combined probe for measuring transonic two-dimensional unsteady flow field Download PDFInfo
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- CN106908191B CN106908191B CN201710136639.6A CN201710136639A CN106908191B CN 106908191 B CN106908191 B CN 106908191B CN 201710136639 A CN201710136639 A CN 201710136639A CN 106908191 B CN106908191 B CN 106908191B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L19/00—Details of, or accessories for, apparatus for measuring steady or quasi-steady pressure of a fluent medium insofar as such details or accessories are not special to particular types of pressure gauges
- G01L19/0092—Pressure sensor associated with other sensors, e.g. for measuring acceleration or temperature
Abstract
The invention belongs to the technical field of temperature and pressure tests, and discloses a dynamic temperature and pressure combined probe for measuring a transonic two-dimensional unsteady flow field, which comprises a probe head and a support rod, wherein the probe head is of a double-cylinder cambered prism structure, and 3 dynamic pressure sensors and 1 dynamic temperature sensor are arranged in the probe head. During measurement, the windward side of the head of the probe comprises a right front cylindrical cambered surface, a left side plane and a right side plane, and the leeward side is a rear cylindrical cambered surface. 3 parts of the windward side 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 method can simultaneously measure the change of the transonic incoming flow temperature, the total pressure, the static pressure, the deflection angle, the Mach number and the two-dimensional velocity along with time through calibrating the calibration of the wind tunnel, and provides a means for efficiently, accurately and comprehensively measuring transonic two-dimensional unsteady 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 dynamic temperature and dynamic pressure measuring device of a transonic two-dimensional unsteady flow field, and particularly relates to a dynamic temperature and pressure combined probe for measuring the transonic two-dimensional unsteady flow field, which is suitable for testing the transonic two-dimensional dynamic flow field between a turbine guider and a movable blade.
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 needs to measure the unsteady velocity field, the pressure field and the temperature field of the transonic 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 transonic two-dimensional flow field at the outlet of the turbine guide vane is abnormal and changes along with the change of the positions of the rotor blade blades, and the existing probe technology can only provide stable 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 provide dynamic pressure, dynamic temperature and dynamic speed data of a measured flow field simultaneously in a transonic two-dimensional dynamic flow field propagation test of a hot spot in a turbine, and provides a dynamic temperature and pressure combined probe for measuring a transonic two-dimensional unsteady flow field, which can measure a high subsonic speed (0.75< Mach number <1.0) and a supersonic speed (1.0< Mach number <1.2) two-dimensional dynamic flow field and measure the temperature, total pressure, static pressure, deflection angle, Mach number and speed change along with time of a transonic two-dimensional flow field at the outlet of a turbine guider, and is suitable for researching an unsteady propagation mechanism of the hot spot in and at the outlet of the turbine guider.
The technical solution of the invention is as follows:
1. the utility model provides a measure dynamic temperature pressure combination probe of transonic 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 double-cylinder cambered prism structure, 3 dynamic pressure sensors and 1 dynamic temperature sensor are arranged in the probe head, and the top surface (3) of the probe head (1) is perpendicular to the rotation axis of the probe supporting rod (2). When the probe is used for measuring, the windward side of the probe head (1) comprises a right front cylindrical cambered surface (4), a left side plane (5) and a right side plane (6), and the leeward side is a rear cylindrical cambered surface (7); the dynamic temperature sensor head (8) is exposed out of the top surface (3); the front cylindrical cambered surface (4), the left plane (5) and the right plane (6) of the probe head (1) are respectively provided with 1 pressure sensing hole which is a middle hole (9), a left hole (10) and a right hole (11), and the 3 pressure sensing holes which are not communicated with each other are respectively communicated with 3 dynamic pressure sensors in the probe head (1).
2. Furthermore, the probe supporting rod (2) is a cylinder, a circular channel is formed in the probe supporting rod, and a circular channel is formed in the probe supporting rod.
3. Furthermore, the central line of a hole (9) in the probe head (1), the central line of the temperature sensor head (8) and the axis of the probe support rod (2) are on the same plane, the left plane (5) and the right plane (6) are symmetrical along the plane, and the left hole (10) and the right hole (11) are symmetrically distributed along the plane.
4. Furthermore, the included angle between the left plane (5) and the right plane (6) is 32-76 degrees, and the arc length of the right front cylindrical arc surface (4) of the probe head (1) is 1-2 millimeters.
5. Further, the dynamic temperature sensor head (8) is exposed to the top surface (3) by 1 mm to 3 mm.
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 middle hole (9), the left hole (10) and the right hole (11) are 0.6 mm to 1.5 mm.
8. Furthermore, cables (12) of 3 dynamic pressure sensors and 1 dynamic temperature sensor in the probe head (1) are led out from the tail of the probe through channels 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 change of the transonic incoming flow temperature, the total pressure, the static pressure, the deflection angle, the Mach number and the two-dimensional velocity along with time through calibrating the calibration of the wind tunnel, and provides a means for efficiently, accurately and comprehensively measuring transonic 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 a transonic 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-right front cylinder cambered surface, 5-left side plane, 6-right side plane, 7-rear cylinder cambered surface, 8-dynamic temperature sensor head, 9-middle hole, 10-left hole, 11-right hole and 12-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 dynamic temperature and pressure combined probe for measuring a transonic two-dimensional unsteady flow field, including a probe head (1) and a support rod (2), where the probe head (1) is a double-cylinder arc prism structure, the diameter of an external circle is 6 mm, the height of the probe head (1) is 30 mm, and 3 dynamic pressure sensors and 1 dynamic temperature sensor are installed in the probe head, and a top surface (3) of the probe head (1) is perpendicular to a rotation axis of the probe support rod (2). When the probe is used for measuring, the windward side of the probe head (1) comprises a right front cylindrical cambered surface (4), a left side plane (5) and a right side plane (6), and the leeward side is a rear cylindrical cambered surface (7); the dynamic temperature sensor head (8) is exposed out of the top surface (3); the front cylindrical cambered surface (4), the left plane (5) and the right plane (6) of the probe head (1) are respectively provided with 1 pressure sensing hole which is a middle hole (9), a left hole (10) and a right hole (11), and the 3 pressure sensing holes which are not communicated with each other are respectively communicated with 3 dynamic pressure sensors in the probe head (1).
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 central line of a hole (9) in the probe head (1), the central line of the temperature sensor head (8) and the axis of the probe supporting rod (2) are on the same plane, the left plane (5) and the right plane (6) are symmetrical along the plane, and the left hole (10) and the right hole (11) are symmetrically distributed along the plane. The distance between the circle center of the left hole (10) and the left side of the right front cylindrical cambered surface (4) is 3 mm, and the distance between the circle center of the right hole (11) and the right side of the right front cylindrical cambered surface (4) is 3 mm.
The included angle between the left plane (5) and the right plane (6) is 45 degrees, and the arc length of the right front cylindrical cambered surface (4) of the probe head (1) is 1 mm.
The dynamic temperature sensor head (8) is exposed to the top surface (3) by 2 mm.
The distance between the center of the center hole (9) and the top surface (3) of the probe head (1) is 2 mm.
The centers of the middle hole (9), the left hole (10) and the right hole (11) are on the same plane, and the diameter is 0.6 mm.
Cables (12) of 3 dynamic pressure sensors and 1 dynamic temperature sensor in the probe head (1) are led out from the tail of the probe through channels in the probe supporting rod (2).
The dynamic temperature and pressure combined probe for measuring the transonic two-dimensional unsteady flow field introduced in the embodiment of the invention can obtain calibration data through transonic speed calibration wind tunnel calibration. When a transonic 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, the obtained transonic speed is used for calibrating wind tunnel calibration data, data processing is carried out, and the change of transonic 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 transonic 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 double-cylinder cambered prism structure, 3 dynamic pressure sensors and 1 dynamic temperature sensor are arranged in the probe head, the top surface (3) of the probe head (1) is perpendicular to the rotation axis of the probe supporting rod (2), the windward side of the probe head (1) during probe measurement comprises a front cylinder cambered surface (4), a left side plane (5) and a right side plane (6), and the leeward side is a rear cylinder cambered surface (7); the dynamic temperature sensor head (8) is exposed out of the top surface (3); 1 pressure sensing holes, namely a middle hole (9), a left hole (10) and a right hole (11), are respectively formed in a right front cylindrical cambered surface (4), a left plane (5) and a right plane (6) 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 head (1);
the probe supporting rod (2) is a cylinder, and a circular channel is formed in the probe supporting rod;
the central line of a hole (9) in the probe head (1), the central line of the temperature sensor head (8) and the axis of the probe support rod (2) are on the same plane, the left plane (5) and the right plane (6) are symmetrical along the plane, and the left hole (10) and the right hole (11) are symmetrically distributed along the plane;
the included angle between the left plane (5) and the right plane (6) is 32-76 degrees, and the arc length of the right front cylindrical arc surface (4) of the probe head (1) is 1-2 mm;
the head (8) of the dynamic temperature sensor is exposed out of the top surface (3) by 1 mm to 3 mm;
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;
the diameters of the middle hole (9), the left hole (10) and the right hole (11) are 0.6 mm to 1.5 mm;
cables (12) of 3 dynamic pressure sensors and 1 dynamic temperature sensor in the probe head (1) are led out from the tail of the probe through channels in the probe supporting rod (2);
the combined probe can measure both high subsonic speed and supersonic speed two-dimensional dynamic flow fields, and simultaneously measure the temperature, total pressure, static pressure, deflection angle, Mach number and speed change along with time of a transonic speed two-dimensional flow field at the outlet of the turbine guider, and is suitable for researching the unsteady propagation mechanism of hot spots in the turbine guider and at the outlet;
the dynamic temperature and pressure combined probe for measuring the transonic two-dimensional unsteady flow field can simultaneously measure the transonic incoming flow temperature, the total pressure, the static pressure, the deflection angle, the Mach number and the change of two-dimensional speed along with time after being calibrated by the wind tunnel, and provides a means for efficiently, accurately and comprehensively measuring transonic two-dimensional unsteady flow field parameters for a turbine experiment.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710136639.6A CN106908191B (en) | 2017-03-09 | 2017-03-09 | Dynamic temperature and pressure combined probe for measuring transonic two-dimensional unsteady flow field |
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| CN201710136639.6A CN106908191B (en) | 2017-03-09 | 2017-03-09 | Dynamic temperature and pressure combined probe for measuring transonic two-dimensional unsteady flow field |
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| CN106908191A CN106908191A (en) | 2017-06-30 |
| CN106908191B true CN106908191B (en) | 2020-11-13 |
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Families Citing this family (1)
| 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 |
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| CN201583369U (en) * | 2009-11-19 | 2010-09-15 | 东方电气集团东方汽轮机有限公司 | Multi-stage turbine test interstage measuring device |
| CN103267626A (en) * | 2013-06-03 | 2013-08-28 | 北京国电龙源环保工程有限公司 | Multifunctional detecting device for flow field measurement and detecting method applying same |
| CN104048808A (en) * | 2013-03-14 | 2014-09-17 | 中国科学院工程热物理研究所 | Dynamic entropy probe |
| CN104713693A (en) * | 2014-12-15 | 2015-06-17 | 中国燃气涡轮研究院 | Pressure-leading type supersonic velocity five-hole probe with orthogonal auxiliary holes |
| CN105588703A (en) * | 2015-12-15 | 2016-05-18 | 中国燃气涡轮研究院 | 12-hole omni-directional probe for subsonic-speed and complex three-dimensional flow field measurement |
| CN105716779A (en) * | 2015-11-02 | 2016-06-29 | 北京航空航天大学 | Dynamic pressure blade type probe |
| CN105716788A (en) * | 2015-11-02 | 2016-06-29 | 北京航空航天大学 | Three-hole transonic speed pressure probe |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105890804B (en) * | 2016-04-08 | 2019-05-17 | 北京航空航天大学 | A method of it improving temperature sensor and measures total airflow temperature precision |
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- 2017-03-09 CN CN201710136639.6A patent/CN106908191B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201583369U (en) * | 2009-11-19 | 2010-09-15 | 东方电气集团东方汽轮机有限公司 | Multi-stage turbine test interstage measuring device |
| CN104048808A (en) * | 2013-03-14 | 2014-09-17 | 中国科学院工程热物理研究所 | Dynamic entropy probe |
| CN103267626A (en) * | 2013-06-03 | 2013-08-28 | 北京国电龙源环保工程有限公司 | Multifunctional detecting device for flow field measurement and detecting method applying same |
| CN104713693A (en) * | 2014-12-15 | 2015-06-17 | 中国燃气涡轮研究院 | Pressure-leading type supersonic velocity five-hole probe with orthogonal auxiliary holes |
| CN105716779A (en) * | 2015-11-02 | 2016-06-29 | 北京航空航天大学 | Dynamic pressure blade type probe |
| CN105716788A (en) * | 2015-11-02 | 2016-06-29 | 北京航空航天大学 | Three-hole transonic speed pressure probe |
| CN105588703A (en) * | 2015-12-15 | 2016-05-18 | 中国燃气涡轮研究院 | 12-hole omni-directional probe for subsonic-speed and complex three-dimensional flow field measurement |
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