Composite five-hole pressure-temperature probe

Abstract

The invention provides a composite five-hole pressure-temperature probe. The probe comprises a total temperature thermocouple, five pressure measuring tubes, four static pressure measuring tubes and four static temperature thermocouples which are arranged in a probe rod body. The front end of the probe rod body is a static parameter section; the rear end of the probe rod body is a leading-out section; the transition section is connected with a pressure measuring head part and the static parameter section; the detection ends of the total temperature thermocouple and the pressure measuring tubesare arranged at the end part of the pressure measuring head part; the detection ends of the static pressure measuring tubes and the static temperature thermocouples are arranged on the side wall of the static parameter section; and all the pressure measuring tubes and thermocouples extend out of the leading-out section. According to the invention, aerodynamic parameters such as the total temperature, the static temperature, the total pressure, the static pressure, the mach number, the three-dimensional flow velocity, the deflection angle and the pitch angle of the airflow under the transonicvelocity and supersonic velocity incoming flow conditions can be simultaneously measured in the same place, the interference of the probe on a flow field is effectively reduced, and accurate measurement is realized.

Description

technical field [0001] The invention relates to the field of pressure, temperature and speed testing, in particular to a composite five-hole pressure-temperature probe. Background technique [0002] The aerodynamic probe is the most important and convenient measurement tool in the turbomachinery wind tunnel experiment. In the prior art, the commonly used five-hole pneumatic pressure probe can only measure the total pressure, static pressure, Mach number, deflection angle and pitch angle of the airflow at the measuring point. For the measurement of the three-dimensional velocity value of the airflow, an additional temperature sensor is required to indirectly calculate the three-dimensional velocity value through the measured total temperature. [0003] In turbomachinery wind tunnel experiments, under low-speed and high-subsonic incoming flow conditions, temperature probes are mostly placed in the stable section of the wind tunnel to measure the airflow temperature, and the t...

AI Technical Summary

Problems solved by technology

However, under the condition of trans- and supersonic incoming flow, due to the shock wave structure in the pressure measuring head of the pneumatic probe, the local entropy increases, and the temperature of the airflow will have a step change. In this case, it is necessary to measure the same measuring point pressure and temperature values ​​at

However, in the existing technology, one way is to use a separate pneumatic pressure probe and a separate temperature probe to measure the aerodynamic parameters at the measuring point in sequence. This method can measure the aerodynamic parameters in the same space but not at the same time. parameters; one way is to combine pressure probes and temperature probes to measure aerodynamic parameters at one time, but most of the combined probes shown in the published literature are two independent probes combined by binding, welding, etc. Together, the two probes are not completely in the same spatial position, it can be considered that they can measure the same time, but not the aerodynamic parameters of the same space

In addition, the geometric dimensions of this probe are larger than ordinary pneumatic probes, which will cause greater disturbance to the flow field

[0004] Therefore, most of the current aerodynamic probes are unable to obtain aerodynamic parameters such as total temperature, static temperature, total pressure, static pressure, Mach number, three-dimensional flow velocity, deflection angle and pitch angle of the same space point at the same time.

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