Hot air deicing total pressure sensor

Abstract

The invention provides a hot air deicing total pressure sensor, and aims to provide a total pressure sensor which is high in hot air energy utilization rate. The hot air deicing total pressure sensoris implemented according to the technical scheme that the total pressure of an incoming flow is conducted through a side hole at the surface of a boss plug (9) arranged in a channel of a total pressure port (6); a heating air flow provided by an engine and a hot air generator flows to an area easy to freeze at the windward front edge of an airspeed tube supporting arm (2) through a lower hot air flowing channel (14) from a hot air interface (4), the heating air flow is disturbed through spoilers (13) arranged adjacent to two sides of the total pressure port, the hot air flow is enhanced in heat transfer through the disturbance, then sequentially gets into a first annular flow channel, a second annular flow channel and a third annular flow channel along an internal cavity of the total pressure port and performs heat exchange in a cyclic mode from the upper side to the lower side and from the lower side to the upper side of the boss plug, and then hot air flow gets into the rear part ofthe sensor through a hot air flow channel (17) and discharged into the atmosphere from an exhaust port (8) opened in a low-pressure area at the lower part of the airspeed tube supporting arm.

Description

technical field [0001] The invention relates to a measuring device for airflow total pressure at the inlet of an aeroengine, and relates to a total pressure sensor mainly used for collecting airflow total pressure information. The invention belongs to the technical field of aero-engine testing. Background technique [0002] When the aircraft is flying in the air, it needs altitude and speed information. One of the ways to obtain the information is the total static pressure sensor (hereinafter referred to as the sensor) installed on the aircraft. The sensor is the input port of the air data system. Accurate measurement of flight parameters and anti-icing and deicing capabilities are two very important functions. In order to ensure the reliability of the measured flight parameters of the sensor, the ability of anti-icing and melting ice is a very important function. The icing problem of the aircraft seriously endangers the safety of the aircraft. The appearance of ice on th...

AI Technical Summary

Problems solved by technology

But both methods have disadvantages, such as limited efficiency of the liquid deicing system, and the gas shroud adds weight and power consumption to the aircraft

Due to the existence of rotational inertia, the two physical quantities cannot be synchronized in time and space, and considering the physical characteristics of the turbulent flow field, there will be a large error between the measurement result and the actual wind vector

When the starting wind speed of the wind direction and wind speed sensors is different, it may even cause completely wrong measurement results

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