CN106908191B - Dynamic temperature and pressure combined probe for measuring transonic two-dimensional unsteady flow field - Google Patents

Abstract

The invention belongs to the technical field of temperature and pressure testing, and discloses a dynamic temperature and pressure combined probe for measuring transonic two-dimensional unsteady flow field. The structure is equipped with 3 dynamic pressure sensors and 1 dynamic temperature sensor. During measurement, the windward surface of the probe head includes the front cylindrical arc surface, the left plane and the right plane, and the leeward surface is the rear cylindrical arc surface. There are 1 pressure sensing holes in each of the 3 parts on the windward side, which are respectively connected to the 3 dynamic pressure sensors in the probe head. The head of the dynamic temperature sensor is exposed on the top surface of the probe head, and the sensor cable passes through the inner channel of the support rod. Extract the probe tail. Compared with the existing pressure probe, the invention can simultaneously measure the temperature, total pressure, static pressure, deflection angle, Mach number and two-dimensional velocity of the transonic flow with time after calibration in the calibration wind tunnel. The experiment provides an efficient, accurate and comprehensive means to measure the parameters of transonic two-dimensional unsteady flow field.

Description

A dynamic temperature-pressure combined probe for measuring transonic two-dimensional unsteady flow field

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 for a transonic two-dimensional unsteady flow field, and in particular relates to a dynamic temperature and pressure combined probe for measuring a transonic two-dimensional unsteady flow field , which is suitable for the test of the transonic two-dimensional dynamic flow field between the turbine guide and the bucket.

Background technique

The presence of hot spots at the turbine inlet of aero-engines and gas turbines will affect the downstream temperature field distribution, and even seriously affect the thermal load and life of turbine blades. To study the propagation mechanism of the hot spot in the turbine guide, it is necessary to measure the unsteady velocity field, pressure field and temperature field of the two-dimensional transonic flow field at the exit of the turbine guide.

At present, three-hole pressure probes and total temperature probes are generally used respectively. With the help of the displacement mechanism installed on the casing, the probes are driven to the measured position for measurement. The three-hole pressure probe can only provide total incoming pressure, static pressure, deflection angle and Mach number, and the total temperature probe can only provide total temperature data.

Using the existing probe measurement technology for experimental research, there are the following problems: 1. The two probes are measured separately, the test time is long, and the test cost is high; 2. The two probes are measured separately, and the probe needs to be replaced during the test. There will be certain changes in the working conditions of the needle and the incoming flow, especially the temperature field will be inconsistent; 3. The position of the measuring point of different probes may be different due to the positioning of the displacement mechanism, and the flow parameter data measured by different probes are definitely not From the same streamline, when these probes are used to measure the data and calculate the speed and other parameters in combination, it will bring data errors, which will bring non-negligible errors to the total measurement results; 4. Due to the rotation of the turbine blades , the transonic two-dimensional flow field at the outlet of the turbine guide is unsteady, and changes with the position of the rotor blades. The existing probe technology can only provide steady-state pressure, temperature and velocity data, and cannot reflect the hot spot in the Unsteady propagation mechanisms within turbines.

SUMMARY OF THE INVENTION

The purpose of the present invention is to solve the problem that the existing probe technology cannot provide the dynamic pressure, dynamic temperature and dynamic velocity data of the measured flow field at the same time in the hot spot in the turbine transonic two-dimensional dynamic flow field propagation test, and invent a method for measuring The combined probe of dynamic temperature and pressure for transonic two-dimensional unsteady flow field can measure both high subsonic (0.75<Mach number<1.0) and supersonic (1.0<Mach number<1.2) two-dimensional dynamic flow field simultaneously. The temperature, total pressure, static pressure, deflection angle, Mach number and velocity of the two-dimensional transonic flow field at the exit of the turbine guide are obtained with time, which is suitable for studying the unsteady propagation mechanism of hot spots in the turbine guide and the exit.

The technical solution of the present invention is:

1. A dynamic temperature and pressure combined probe for measuring transonic two-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 The double-cylindrical arc-surface prism structure is equipped with three dynamic pressure sensors and one dynamic temperature sensor inside, and the top surface (3) of the probe head (1) is perpendicular to the axis of rotation of the probe support rod (2). During probe measurement, the windward surface of the probe head (1) includes a front cylindrical arc surface (4), a left plane (5) and a right plane (6), and the leeward surface is the rear cylindrical arc surface (7); dynamic The temperature sensor head (8) is exposed on the top surface (3); there is a pressure point on the front cylindrical arc surface (4), the left plane (5) and the right plane (6) of the probe head (1). The sensing holes are the middle hole (9), the left hole (10), and the right hole (11). These three pressure-sensing holes that do not communicate with each other are respectively connected with the three dynamic pressure sensors in the probe head (1). Connected.

2. Further, the probe support rod (2) is a cylinder, and a circular channel is opened in its interior, and a circular channel is opened in its interior.

3. Further, the center line of the hole (9) in the probe head (1), the center line of the temperature sensor head (8) and the axis of the probe support rod (2) are on the same plane, and the left plane (5) is on the same plane. The right plane (6) is symmetrical along this plane, and the left hole (10) and the right hole (11) are symmetrically distributed along this plane.

4. Further, the angle between the left plane (5) and the right plane (6) is 32° to 76°, and the arc length of the front cylindrical arc surface (4) of the probe head (1) is 1 mm to 2 mm. mm.

5. Further, the head (8) of the dynamic temperature sensor is exposed from the top surface (3) by 1 mm to 3 mm.

6. Further, the distance between the center of the 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. Further, cables (12) of three dynamic pressure sensors and one dynamic temperature sensor in the probe head (1) are led out from the probe tail 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 temperature, total pressure, static pressure, deflection angle, Mach number and two-dimensional velocity of the transonic flow with time after calibration in the calibration wind tunnel. The experiment provides an efficient, accurate and comprehensive means to measure the parameters of transonic two-dimensional unsteady flow field.

Description of drawings

FIG. 1 is a schematic structural diagram of a dynamic temperature-pressure combined 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 plan view of FIG. 1 .

Among them: 1-probe head, 2-probe support, 3-top surface, 4-front cylindrical arc surface, 5-left plane, 6-right plane, 7-back cylindrical arc, 8- Dynamic temperature sensor head, 9-center hole, 10-left hole, 11-right hole, 12-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 dynamic temperature and pressure combined probe for measuring transonic two-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 double-cylindrical arc prism structure, the diameter of the circumscribed circle is 6 mm, and the height of the probe head (1) is 30 mm. It is equipped with 3 dynamic pressure sensors, 1 dynamic temperature sensor, and the probe head ( The top surface (3) of 1) is perpendicular to the axis of rotation of the probe support rod (2). During probe measurement, the windward surface of the probe head (1) includes a front cylindrical arc surface (4), a left plane (5) and a right plane (6), and the leeward surface is the rear cylindrical arc surface (7); dynamic The temperature sensor head (8) is exposed on the top surface (3); there is a pressure point on the front cylindrical arc surface (4), the left plane (5) and the right plane (6) of the probe head (1). The sensing holes are the middle hole (9), the left hole (10), and the right hole (11). These three pressure sensing holes that are not connected to each other are respectively connected with the three dynamic pressure sensors in the probe head (1). Connected.

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 center line of the hole (9) in the probe head (1), the center line of the temperature sensor head (8) and the axis of the probe support rod (2) are on the same plane, and the left plane (5) and the right plane ( 6) Symmetrical along the plane, the left hole (10) and the right hole (11) are symmetrically distributed along the plane. The distance between the center of the left hole (10) and the left side of the front cylindrical arc surface (4) is 3 mm, and the distance between the center of the right hole (11) and the right side of the front cylindrical arc surface (4) is 3 mm.

The angle between the left plane (5) and the right plane (6) is 45°, and the arc length of the front cylindrical arc surface (4) of the probe head (1) is 1 mm.

The head (8) of the dynamic temperature sensor is exposed by 2 mm from the top surface (3).

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.

The cables (12) of three dynamic pressure sensors and one dynamic temperature sensor in the probe head (1) are led out from the probe tail through the inner channel of the probe support rod (2).

The dynamic temperature and pressure combined probe for measuring the transonic two-dimensional unsteady flow field introduced in the embodiment of the present invention can be calibrated by the transonic calibration wind tunnel, and the calibration data can be obtained. When actually measuring the transonic two-dimensional unsteady flow field, the three dynamic pressure sensors and one dynamic temperature sensor of the dynamic temperature and pressure combination probe simultaneously measure the unsteady pressure and unsteady temperature data they feel, and use the obtained data. Transonic calibration wind tunnel calibration data, data processing, can obtain the temperature, total pressure, static pressure, deflection angle, Mach number and two-dimensional velocity of the transonic flow with time.

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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