Hot air deicing total pressure sensor

A sensor, hot gas technology, applied in instruments, measuring fluid pressure, measuring devices, etc., can solve the problems of limited efficiency of liquid de-icing system, unsynchronized time and space, increase aircraft weight and power consumption, etc., to improve energy Utilization, light weight, simple and reliable structure

Pending Publication Date: 2018-01-05
CHENGDU KAITIAN ELECTRONICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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 consider

Method used

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Examples

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Embodiment Construction

[0019] refer to Figure 1-Figure 4, in the embodiment described below, a hot gas deicing total pressure sensor, including a cone-shaped opening probe 1 with a trumpet-shaped total pressure port 6, fixedly connected to the space velocity that extends obliquely from the mounting base 3 Pipe arm 2 and the hot gas port 4 and total pressure port 5 communicating with the pitot arm (2), wherein the pitot arm 2 is fixedly connected to the square mounting seat with 6 countersunk holes 3, the hot gas port 4 and the total pressure port 5 have flared straight-through pipe joints. The trumpet-shaped total pressure port 6 is located at the end of the cone-shaped opening probe 1, and the elbow of the cone-shaped opening probe 1 is formed with a drainage hole 7, and an exhaust port 8 is provided on the tail of the support arm. The total pressure port 6 adopts a horn-shaped sharp-edged design, and the horn-shaped opening angle is 30°-45°, and the total pressure of the airflow can be felt with...

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Abstract

The invention proposes a total pressure sensor for hot gas deicing, aiming to provide a total pressure sensor with high utilization rate of hot gas energy. The present invention is realized through the following technical solutions: the total pressure of the incoming flow is conducted through the side hole on the surface of the built-in boss plug (9) of the total pressure port (6); the heated air flow provided by the engine and the hot gas generator is transferred from the hot gas interface ( 4) Flow through the lower hot runner (14) to the area prone to freezing on the windward front of the pitot arm (2), and interfere with the spoilers (13) arranged on both sides of the total pressure port, after the disturbance enhances heat transfer , enter the first, second and third shape flow passages in turn along the internal connection cavity of the total pressure port, circulate the heat exchange hot air from the upper and lower sides of the boss plug, and from the lower side to the upper side, and enter the receiving flow channel through the hot air flow channel (17). At the rear of the sensor, it is discharged into the atmosphere from the exhaust port (8) opened in the low-pressure area of ​​the lower part of the pitot 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...

Claims

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Application Information

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IPC IPC(8): G01L19/00G01L19/06
Inventor 周毅朱世民周游吉孟江欧帅
Owner CHENGDU KAITIAN ELECTRONICS
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