CN106840512B - Four-hole dynamic pressure probe for measuring supersonic three-dimensional unsteady flow field - Google Patents

Abstract

The invention belongs to the technical field of pressure testing, and discloses a four-hole dynamic pressure probe for measuring a supersonic three-dimensional unsteady flow field, which comprises a probe head and a support rod, wherein the probe head is of a wedge-top triangular prism structure, 4 dynamic pressure sensors are packaged in the probe head, the windward side of the probe head comprises a wedge-top inclined plane, a left side surface and a right side surface during measurement, 1 pressure sensing hole is respectively arranged on the front edge of the junction of the wedge-top inclined plane, the left side surface, the right side surface and the left and right side surfaces of the probe head, and is respectively communicated with the 4 dynamic pressure sensors, and cables of the 4 dynamic pressure sensors are led out of the tail part of the probe through an inner channel of the support. Compared with the existing pressure probe, the method can simultaneously measure the change of total pressure, static pressure, deflection angle, pitch angle and Mach number of the ultrasonic incoming flow along with time after calibration of the wind tunnel, and provides a means for efficiently and accurately measuring the parameters of the ultrasonic three-dimensional unsteady flow field for a turbine experiment.

Description

A four-hole dynamic pressure probe for measuring supersonic three-dimensional unsteady flow field

technical field

The invention belongs to the technical field of pressure testing, relates to a dynamic pressure measuring device for a supersonic three-dimensional unsteady flow field, and in particular relates to a four-hole dynamic pressure probe for measuring a supersonic three-dimensional unsteady flow field, which is suitable for the inlet, outlet and Testing of interstage supersonic 3D dynamic flow fields.

Background technique

The three-dimensional flow field between supersonic compressor stages is inherently unsteady due to fluid viscosity, shock waves, rotor rotation, the existence of blade tip clearance, and the staggered arrangement of moving and stationary blade rows. The dynamic characteristics of the flow field cannot be measured by the conventional steady-state pressure probe. The hot wire anemometer can measure the dynamic velocity signal, but cannot measure the pressure information. For turbomachines, researchers prefer to obtain dynamic pressure distributions between stages and rotor exits for design validation and flow field diagnostics to improve machine performance.

At present, due to the lack of practical dynamic testing technology in engineering, steady-state measurement technology such as five-hole pressure probe is generally used in engineering. With the help of the displacement mechanism installed on the casing, the pressure probe is driven to the measured position to measure the supersonic three-dimensional flow field. . The steady-state five-hole pressure probe has a long pressure-inducing tube inside, and the cavity effect formed damps the dynamic pressure information of the measured flow field, and cannot obtain the total pressure, static pressure, and static pressure that truly reflect the measured flow field. The variation law of yaw angle, pitch angle and Mach number with time cannot measure the parameter distribution of the rotor outlet from the pressure surface to the suction surface.

SUMMARY OF THE INVENTION

The technical problem to be solved by the present invention is: in view of the lack of three-dimensional dynamic flow field measurement means between supersonic compressor stages in the current engineering, a four-hole dynamic pressure probe for measuring supersonic three-dimensional unsteady flow field is invented to provide a It is a practical technical method for measuring the supersonic three-dimensional unsteady flow field between supersonic compressor stages.

The technical solution of the present invention is:

1. A four-hole dynamic pressure probe for measuring supersonic three-dimensional unsteady flow field, characterized in that it comprises a probe head (1) and a support rod (2), and the probe head (1) is a wedge The top triangular prism structure is equipped with 4 dynamic pressure sensors. When the probe is measuring, the windward side of the probe head (1) includes the wedge top slope (3), the symmetrical left side (4) and the wedge top triangular prism. The right side (5); on the wedge top slope (3) of the probe head (1), there is a pressure sensing hole, which is the upper hole (6), on the left side (4) of the probe head (1). ), the right side (5) and the front edge of the junction of the two sides are each provided with a pressure-sensing hole, which are the left hole (7), the right hole (8), and the middle hole (9). The disjoint pressure sensing holes are respectively communicated with the four dynamic pressure sensors in the probe head (1).

2. Further, the probe support rod (2) is a columnar structure, which can be a cylinder or a triangular prism, and a circular channel is opened inside it.

3. Further, the angle between the left side (4) and the right side (5) of the probe head (1) is 24° to 76°.

4. Further, the included angle between the front edge line at the junction of the left side surface (4) and the right side surface (5) of the probe head (1) and the slope of the wedge top is 35° to 54.5°.

5. Further, the distance between the upper hole (6) on the wedge top inclined surface (3) and the lowest point of the wedge top inclined surface (3) is 1 mm to 5 mm.

6. Further, the distance between the middle hole (9) and the lowest point of the wedge top slope (3) is 1 mm to 3 mm.

7. Further, the center line of the upper hole (6) of the probe head (1), the center line of the middle hole (9), and the front edge line at the junction of the left side (4) and the right side (5) are on the same plane , the left side (4) and the right side (5) are symmetrical along the plane, the left hole (7) and the right hole (8) are symmetrically distributed along the plane, and the back of the probe head (10) is perpendicular to the plane.

8. Further, the diameters of the upper hole (6), the left hole (7), the right hole (8) and the middle hole (9) are 0.6 mm to 1.5 mm.

9. Further, the cable (11) of the dynamic pressure sensor is led out from the end of the probe through the inner channel of the probe support rod (2).

The beneficial effects of the present invention are:

Compared with the existing pressure probe, the invention can simultaneously measure the changes of the total pressure, static pressure, deflection angle, pitch angle and Mach number of the supersonic flow with time after the calibration of the wind tunnel. An efficient and accurate method for measuring ultrasonic three-dimensional unsteady flow field parameters is proposed.

Description of drawings

FIG. 1 is a schematic structural diagram of a four-hole dynamic pressure probe for measuring a supersonic three-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 view from the direction A of FIG. 2 .

Among them: 1- Probe head, 2- Probe support, 3- Wedge top slope, 4- Left side, 5- Right side, 6- Upper hole, 7- Left hole, 8- Right hole, 9 -Mid hole, 10-Probe head back, 11-Cable.

Detailed ways

The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

As shown in FIG. 1 , a four-hole dynamic pressure probe for measuring supersonic three-dimensional unsteady flow field is introduced in this embodiment, including a probe head (1), a support rod (2), a probe head ( 1) It is a wedge-top triangular prism structure, the diameter of the circumscribed circle is 6 mm, the height of the probe head (1) is 30 mm, and 4 dynamic pressure sensors are installed inside it. When the probe is measured, the probe head (1) windward side Including the wedge top slope (3), symmetrical left side (4) and right side (5) of the wedge top triangular prism; on the wedge top slope (3) of the probe head (1), there is a pressure sensor The hole is the upper hole (6), and one pressure-sensing hole is opened on the left side (4), the right side (5) and the front edge of the junction of the two side surfaces of the probe head (1). The left hole (7), the right hole (8), and the middle hole (9), these four pressure-sensing holes that do not communicate with each other are respectively communicated with the four dynamic pressure sensors in the probe head (1).

The probe support rod (2) is a cylinder with a diameter of 8 mm, and a circular channel with a diameter of 5 mm is opened inside.

The angle between the left side (4) and the right side (5) of the probe head (1) is 40°.

The leading edge line at the junction of the left side (4) and the right side (5) of the probe head (1) has an included angle of 45° with the slope of the wedge top.

The distance between the upper hole (6) on the wedge top slope (3) and the lowest point of the wedge top slope (3) is 2 mm.

The distance between the middle hole (9) and the lowest point of the wedge top slope (3) is 1 mm.

The center line of the upper hole (6) of the probe head (1), the center line of the middle hole (9), and the front edge line at the junction of the left side (4) and the right side (5) are on the same plane, and the left side (4) The right side surface (5) is symmetrical along the plane, the left hole (7) and the right hole (8) are symmetrically distributed along the plane, and the back surface (10) of the probe head is perpendicular to the plane.

The diameter of the upper hole (6), the left hole (7), the right hole (8) and the middle hole (9) is 0.6 mm.

The centers of the left hole (7), the right hole (8), and the middle hole (9) are on the same plane, and the center of the left hole (7) is in line with the front edge of the junction of the left side (4) and the right side (5). The distance is 3 mm, and the distance between the center of the right hole (8) and the front edge line at the junction of the left side (4) and the right side (5) is 3 mm.

The cable (11) of the dynamic pressure sensor is led out from the end of the probe through the inner channel of the probe support rod (2).

The four-hole dynamic pressure probe for measuring the supersonic three-dimensional unsteady flow field introduced in the embodiment of the present invention can obtain calibration data after being calibrated in the supersonic calibration wind tunnel. When actually measuring the supersonic three-dimensional unsteady flow field, the four dynamic pressure sensors of the four-hole dynamic pressure probe simultaneously measure the unsteady pressure data they feel, and use the obtained supersonic calibration wind tunnel calibration data for data processing. , the changes of total pressure, static pressure, deflection angle, pitch angle and Mach number with time of ultrasonic three-dimensional unsteady incoming flow can be obtained.

Claims (2)

1. A four-hole dynamic pressure probe measuring supersonic three-dimensional unsteady flow field, characterized in that: comprising a probe head (1) and a support rod (2), and the probe head (1) is a wedge The top triangular prism structure is equipped with 4 dynamic pressure sensors. When the probe is measured, the windward side of the probe head (1) includes the wedge top slope (3) and the symmetrical left side (4) of the wedge top triangular prism. and the right side (5); on the wedge top slope (3) of the probe head (1), there is a pressure sensing hole, which is the upper hole (6); On the probe head (1), the left side (4), the right side (5) and the front edge of the junction of the two side faces are respectively provided with one pressure sensing hole, which are respectively the left hole (7) and the right hole ( 8), the middle hole (9), these 4 pressure sensing holes that do not communicate with each other are respectively connected with the 4 dynamic pressure sensors in the probe head (1); The probe support rod (2) is a columnar structure, and a circular channel is opened inside it; The angle between the left side (4) and the right side (5) of the probe head (1) is 76°; The front edge line at the junction of the left side surface (4) and the right side surface (5) of the probe head (1) has an included angle of 35° to 54.5° with the slope of the wedge top; The distance between the upper hole (6) on the wedge top inclined surface (3) and the lowest point of the wedge top inclined surface (3) is 1 mm to 5 mm; The distance between the middle hole (9) and the lowest point of the wedge top slope (3) is 1 mm to 3 mm; The center line of the upper hole (6) of the probe head (1), the center line of the middle hole (9), and the front edge line at the junction of the left side surface (4) and the right side surface (5) are on the same plane, and the left side surface (4) is on the same plane. The 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, and the back surface (10) of the probe head is perpendicular to the plane; The diameters of the upper hole (6), the left hole (7), the right hole (8) and the middle hole (9) are 0.6 mm to 1.5 mm; The cable (11) of the dynamic pressure sensor is led out from the end of the probe through the inner channel of the probe support rod (2). 2 . The probe according to claim 1 , wherein the probe support rod ( 2 ) is a cylinder or a triangular prism. 3 .

Images