Combined type blade profile probe measuring method for inlet airflow parameters of adjustable stationary blade

Abstract

The invention relates to a combined type blade profile probe measuring method used for measuring inlet airflow parameters of an adjustable stationary blade between aviation multistage axial compressorstages. Conventional blade profile probes and blade profile probes with special drift angles are effectively combined, at least one blade profile probe has the drift angle in the installation process, the radial positions and the measure point quantity of the blade profile probes which are installed with the drift angles and have a relative direction angle difference theta with respect to measuring points of the conventionally-mounted blade profile probes are the same as those of the conventionally-mounted blade profile probes according to needs, and at least one blade profile probe having the drift angle exists at the same radial position; the theta is not large than 20 degrees, is not larger than the insensitive angular range alphaw of the blade profile probes and is not less than 10 degrees, and the conventionally-mounted blade profile probes are used for measuring under the working conditions with the relative conversion rotation speed being 90% or more; and the blade profile probes having the drift angles are used for measuring under the working conditions with the relative conversion rotation speed being 85% or less. The method effectively avoids interference generated by the low-speed blade profile probes on the flow field of a suction surface of the stationary blade, and accordingly reduces the negative influence of the low-speed blade profile probes on the aerodynamicperformance of a compressor.

Description

technical field [0001] The present invention relates to the research field of aerodynamic performance test of multi-stage axial flow compressors of aero-engines, and proposes a combined airfoil probe for accurately measuring airflow parameters of adjustable stator blade inlets of multi-stage axial flow compressors within a wide range of operating speed variations Measurement methods. Background technique [0002] In order to develop advanced axial flow compressor components for aero-engines, it is necessary to have a detailed understanding of the internal complex flow information of the axial flow compressor under design conditions and non-design conditions during the design stage, and test measurements are recognized as the basis for obtaining axial compressor aerodynamics. Performance parameters are the most effective and reliable technical means. Due to the staggered arrangement of the rotors and stator blades of the axial flow compressor, the flow channel space is narro...

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the problem that the insensitive angle range of the blade probe on the adjustable vane of the multi-stage axial flow compressor cannot adapt to the measurement of air flow parameters in all working conditions, and the conventional blade probe and the blade with deflection angle The probes are effectively combined (that is, the combined airfoil probe measurement method), in which the conventional airfoil probe is only used for high-speed area measurement, and the deflection-angled airfoil probe is used for medium and low-speed area measurement, so that Realize the complete and accurate measurement of airflow parameters at the inlet of the adjustable vane of the compressor within a wide range of operating speed changes

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