CN106940242B - Three-hole dynamic pressure probe for measuring transonic two-dimensional unsteady flow field - Google Patents
Three-hole dynamic pressure probe for measuring transonic two-dimensional unsteady flow field Download PDFInfo
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- CN106940242B CN106940242B CN201710139430.5A CN201710139430A CN106940242B CN 106940242 B CN106940242 B CN 106940242B CN 201710139430 A CN201710139430 A CN 201710139430A CN 106940242 B CN106940242 B CN 106940242B
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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
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Abstract
The invention belongs to the technical field of pressure testing, and discloses a three-hole dynamic pressure probe for measuring a transonic two-dimensional unsteady flow field. During measurement, the windward side of the head of the probe comprises a front plane, a left side face and a right side face, and the leeward side is a rear plane. 3 parts on 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, and 3 dynamic pressure sensor cables are 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 total pressure, the static pressure, the deflection angle and the Mach number of the transonic incoming flow along with the time through calibrating the calibration of the wind tunnel, and provides a means for efficiently and accurately measuring transonic two-dimensional unsteady flow field parameters for a turbine experiment.
Description
Technical Field
The invention belongs to the technical field of pressure testing, relates to a dynamic pressure measuring device of a transonic two-dimensional unsteady flow field, and particularly relates to a three-hole dynamic pressure probe for measuring the transonic two-dimensional unsteady flow field, which is suitable for testing a transonic two-dimensional dynamic flow field at a movable blade outlet of a centrifugal compressor.
Background
The problem of the interference of moving blades and static blades in a centrifugal compressor is researched, and a two-dimensional transonic unsteady flow field between a moving blade outlet and a diffuser needs to be measured. The dynamic characteristics of a flow field cannot be measured by adopting a conventional steady-state pressure probe, a dynamic speed signal can be measured by a hot wire anemometer, but pressure information cannot be measured, and the hot wire is easy to damage in a transonic environment. For turbomachines, researchers prefer to obtain dynamic pressure profiles at the bucket outlets for validating design and flow field diagnostics in order to improve machine performance.
At present, because of the lack of a practical dynamic testing technology of engineering, the engineering generally adopts a stable state measuring technology such as a three-hole pressure probe and the like, and drives the pressure probe to go to a measured position by means of a displacement mechanism arranged on a casing so as to measure a transonic speed two-dimensional flow field. Because a longer pressure guiding pipe exists in the stable three-hole pressure probe, the formed cavity effect damps dynamic pressure information of the measured flow field, and the change rule of the total pressure, the static pressure, the deflection angle and the Mach number of the measured flow field along with time cannot be truly reflected.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: aiming at the problem that the transonic speed two-dimensional dynamic flow field measurement means for researching the interference phenomenon of the movable blade and the fixed blade in the centrifugal compressor in the current engineering is lack, the invention provides the three-hole dynamic pressure probe for measuring the transonic speed two-dimensional unsteady flow field, and provides the technical means for measuring the two-dimensional transonic speed unsteady flow field between the movable blade outlet and the diffuser of the centrifugal compressor which is practical in the engineering.
The technical solution of the invention is as follows:
1. the utility model provides a three hole dynamic pressure probes of measurement transonic speed two-dimensional unsteady flow field which characterized in that: the probe comprises a probe head (1) and a support rod (2), wherein the probe head (1) is of a quadrangular prism structure, 3 dynamic pressure sensors are arranged in the probe head, the windward side of the probe head (1) during probe measurement comprises a front plane (3), a left side surface (4) and a right side surface (5), and the leeward side is a rear plane (6); 1 pressure sensing holes, namely a left hole (7), a right hole (8) and a middle hole (9), are respectively formed in the left side surface (4), the right side surface (5) and the front plane (3) 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 top surface (10) of the probe head (1) is vertical to the axis of the probe supporting rod (2).
2. Furthermore, the probe supporting rod (2) is a cylinder, and a circular channel is formed in the probe supporting rod.
3. Furthermore, the central line of the hole (9) in the probe head (1) and the axis of the probe supporting rod (2) 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.
4. Furthermore, the included angle between the left side surface (4) and the right side surface (5) is 36-72 degrees, and the width of the front plane (3) of the probe head (1) is 1-2 mm.
5. 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.
6. 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.
7. Furthermore, cables (11) of 3 dynamic pressure sensors 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 total pressure, the static pressure, the deflection angle and the Mach number of the transonic two-dimensional unsteady incoming flow along with the time through calibrating the calibration of the wind tunnel, and provides a means for efficiently and accurately measuring transonic two-dimensional unsteady flow field parameters for a turbine experiment.
Drawings
Fig. 1 is a schematic structural diagram of a three-hole dynamic pressure 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-front plane, 4-left side, 5-right side, 6-rear plane, 7-left hole, 8-right hole, 9-middle hole, 10-top surface, 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 present embodiment introduces a three-hole dynamic pressure probe for measuring a transonic two-dimensional unsteady flow field, which includes a probe head (1) and a support rod (2), wherein the probe head (1) is of a quadrangular 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 are installed inside the probe head (1).
When the probe is used for measurement, the windward side of the head (1) of the probe comprises a front plane (3), a left side surface (4) and a right side surface (5), and the leeward side is a rear plane (6). The left side surface (4), the right side surface (5) and the front plane (3) of the probe head (1) are respectively provided with 1 pressure sensing hole which is a left hole (7), a right hole (8) and a middle hole (9) and is respectively communicated with 3 dynamic pressure sensors in the probe head (1). The top surface (10) of the probe head (1) is vertical to the axis of the probe supporting rod (2).
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) and the axis of the probe supporting rod (2) are on the same plane, the left side surface (4) and the right side surface (5) are symmetrical along the plane, the left hole (7) and the right hole (8) are symmetrically distributed along the plane, the distance between the circle center of the left hole (7) and the left side of the front plane (3) is 3 mm, and the distance between the circle center of the right hole (8) and the right side of the front plane (3) is 3 mm.
The included angle of the left side surface (4) and the right side surface (5) is 45 degrees, and the front plane (3) of the probe head (1) is 1 mm wide.
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 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 3 dynamic pressure sensors in the probe head (1) are led out from the tail of the probe through channels in the probe supporting rod (2).
The three-hole dynamic pressure probe for measuring the transonic two-dimensional unsteady flow field introduced in the embodiment of the invention can obtain calibration data through transonic calibration of the wind tunnel. When a transonic two-dimensional unsteady flow field is actually measured, the 3 dynamic pressure sensors of the three-hole dynamic pressure probe simultaneously measure unsteady pressure data sensed by the three-hole dynamic pressure probe, and the obtained transonic speed calibration wind tunnel calibration data is utilized to perform data processing, so that the changes of the total pressure, the static pressure, the deflection angle and the Mach number of transonic two-dimensional unsteady incoming flow along with time can be obtained.
Claims (1)
1. The utility model provides a three hole dynamic pressure probes of measurement transonic speed two-dimensional unsteady flow field which characterized in that: the probe comprises a probe head (1) and a support rod (2), wherein the probe head (1) is of a quadrangular prism structure, 3 dynamic pressure sensors are arranged in the probe head, the windward side of the probe head (1) during probe measurement comprises a front plane (3), a left side surface (4) and a right side surface (5), and the leeward side is a rear plane (6); 1 pressure sensing holes, namely a left hole (7), a right hole (8) and a middle hole (9), are respectively formed in the left side surface (4), the right side surface (5) and the front plane (3) 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 top surface (10) of the probe head (1) is vertical to the axis of the probe supporting rod (2);
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) and the axis of the probe supporting rod (2) 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 between the left side surface (4) and the right side surface (5) is 45 degrees, and the front plane (3) of the probe head (1) is 1 mm wide;
the distance between the center of the middle hole (9) and the top surface (3) of the probe head (1) is 2 mm;
the diameters of the left hole (7), the right hole (8) and the middle hole (9) are 0.6 mm;
cables (11) of 3 dynamic pressure sensors in the probe head (1) are led out from the tail of the probe through channels in the probe supporting rod (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710139430.5A CN106940242B (en) | 2017-03-10 | 2017-03-10 | Three-hole dynamic pressure probe for measuring transonic two-dimensional unsteady flow field |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710139430.5A CN106940242B (en) | 2017-03-10 | 2017-03-10 | Three-hole dynamic pressure probe for measuring transonic two-dimensional unsteady flow field |
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| Publication Number | Publication Date |
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| CN106940242A CN106940242A (en) | 2017-07-11 |
| CN106940242B true CN106940242B (en) | 2020-04-28 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011148094A1 (en) * | 2010-05-25 | 2011-12-01 | Turbomeca | Device for multipoint acquisition/distribution of fluid, in particular probe for tapping pressure 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 |
| 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 |
-
2017
- 2017-03-10 CN CN201710139430.5A patent/CN106940242B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011148094A1 (en) * | 2010-05-25 | 2011-12-01 | Turbomeca | Device for multipoint acquisition/distribution of fluid, in particular probe for tapping pressure 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 |
| 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 |
Non-Patent Citations (1)
| Title |
|---|
| 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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