Four-hole pressure airfoil probe

Abstract

The invention belongs to the aero-engine pressure test technical field and discloses a four-hole pressure airfoil probe. The four-hole pressure airfoil probe comprises probes, a blade and pressure guide tubes; the probes are cylinders with circular truncated cone-shaped heads; the number of the probes is determined according to measurement requirements; at least three probes should be adopted and are fixed at measurement positions of the blade which extend towards different directions; one pressure sensing hole and three pressure sensing holes are formed at the center of the top surface and side surface of the circular truncated cone of each probe respectively, wherein the four pressure sensing holes are communicated with four pressure guide tubes encapsulated in the probe respectively; and the four pressure guide tubes are fixed at the surface of the blade or inside the blade and are led out from the root portion of the blade. After being calibrated by a calibration wind tunnel, the four-hole pressure airfoil probe can simultaneously measure the total pressure, static pressure, airflow angles and Mach numbers of incoming flows of a plurality of spatial positions and is suitable for measuring the distribution of the incoming flow parameters of inter-stage three-dimensional flow fields of an aero-engine along the height direction of the blade. Compared with ordinary airfoil probes, the four-hole pressure airfoil probe of the invention can measure more flow field parameters such as airflow angles and Mach numbers, and has the advantages of small influence on measured flow fields, high safety and high reliability and the like of the airfoil probes.

Description

Technical field [0001] The invention belongs to the technical field of aeroengine pressure testing, and relates to a three-dimensional flow field pressure measuring device, in particular to a four-hole pressure blade probe, which is suitable for measuring the airflow angle, total pressure, static pressure and Mach number of the inter-stage of the engine. The distribution of the blade height. [0002] Compared with the existing four-hole pressure probe, it does not need to use the probe displacement mechanism to change the position of the measuring point, and can complete the three-dimensional flow field measurement between stages in an instant, reducing the test cost; compared with the ordinary total pressure leaf probe , Can not only measure the total pressure, but also measure the parameters such as the incoming airflow angle, static pressure and Mach number. Background technique [0003] Aeroengine experiments often need to measure the three-dimensional flow field parameters be...

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Problems solved by technology

[0006] The technical problem to be solved by the present invention is: in the narrow space between the stages of the aeroengine, the porous pressure probe cannot complete the measurement of the distribution of the field parameters between the test piece stages along the blade height direction within a few seconds. Aiming at the problem of not being able to measure three-dimensional parameters such as the airflow angle and Mach number of the incoming flow, a four-hole pressure vane probe was invented, which can simultaneously measure the incoming flow parameters at multiple spatial positions, which can shorten the measurement time to the greatest extent and complete the test piece The measurement of the airflow angle, total pressure, static pressure and Mach number distribution along the blade height direction between the stages, reducing the test cost

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