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An absolute pressure fiber-optic silicon carbide high temperature resistant aviation pressure sensor

A Faper silicon carbide and pressure sensor technology, which is applied in the field of absolute pressure fiber Faber silicon carbide high temperature resistant pressure sensor and aviation pressure sensor manufacturing. The effect of low characteristics, fast response speed and good reliability

Active Publication Date: 2020-04-10
BEIHANG UNIV +2
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the working temperature in areas such as the combustion chamber of aero-engines is higher than 1000°C, and the indirect measurement method of placing pressure sensors in low-temperature areas is currently commonly used, which cannot realize dynamic monitoring of pressure changes

Method used

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  • An absolute pressure fiber-optic silicon carbide high temperature resistant aviation pressure sensor
  • An absolute pressure fiber-optic silicon carbide high temperature resistant aviation pressure sensor
  • An absolute pressure fiber-optic silicon carbide high temperature resistant aviation pressure sensor

Examples

Experimental program
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Effect test

Embodiment 1

[0104] The full SiC structure sensing head designed by the present invention is applied to the measurement of dynamic pressure and flow field characteristics in the high-temperature area of ​​the aero-engine. In order to be installed with the devices in the high-temperature area of ​​the aero-engine, a molybdenum package seat 5 and a molybdenum package body are specially designed. 6. The SiC sensing diaphragm 1 and SiC substrate 2 are installed under the zirconia base 3, one end of the sapphire optical fiber 4 is bonded to the SiC substrate 2, and the zirconia base 3 is installed in the countersunk cavity 5C of the molybdenum package base 5 Among them, a molybdenum package body 6 is threadedly connected to the bottom of the molybdenum package base 5;

[0105] According to the sensor obtained in Example 1, the pressure measurement is carried out in a high-temperature environment. The ambient temperature is 1000 ° C, the measurement range is 0-1 MPa, and the Fappon cavity length...

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Abstract

The present invention discloses an absolute pressure fiber fabry-perot silicon carbide heat-resistant aviation pressure sensor. A sensing head in the sensor employs a total SiC structure of a siliconcarbide sensing mebrane and a silicon carbide substrate to achieve vacuum fabry-perot cavity structure through direct binding; the sensor provided by the invention comprises a silicon carbide sensingmebrane, a silicon carbide substrate, optical fibers, a molybdenum package seat and a molybdenum package body; the SiC sensing mebrane and the SiC substrate are installed below a zirconium oxide substrate, one end of the optical fibers is bonded on the SiC substrate, the zirconium oxide substrate is installed in a countersunk head cavity of the molybdenum package seat, and the molybdenum package body is in threaded connection with the lower portion of the molybdenum package seat; and the other end of the optical fibers passes through a B center through hole on the molybdenum package seat. Theabsolute pressure fiber fabry-perot silicon carbide heat-resistant aviation pressure sensor is suitable for the in-situ real-time measurement of the aviation engine high-temperature dynamic pressure and flow field features, and is miniaturized, high in precision and resistant to electromagnetic interference.

Description

technical field [0001] The invention relates to a pressure sensor, more particularly to an absolute pressure fiber-optic silicon carbide high-temperature-resistant pressure sensor, which belongs to the technical field of aviation pressure sensor manufacturing. Background technique [0002] Aeroengine technology is known as the "Pearl in the Crown" of modern industry. It is an important symbol of a country's technological, industrial, economic and national defense strength, and its performance determines the performance of the aircraft. With the development of aero-engines towards high boost ratio, high turbine inlet temperature, high thrust-to-weight ratio, and high reliability, how to realize the measurement of dynamic pressure and flow field characteristics in high-temperature areas of aero-engines under complex and changeable conditions, so as to further It is extremely important to grasp its changing law to realize the control and adjustment of the engine. However, the ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01L23/06
CPCG01L23/06
Inventor 蒋永刚李健张德远黄漫国刘德峰梁晓波
Owner BEIHANG UNIV
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