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Propeller blade leading edge assembly

A technology for propellers and blades, applied in propellers, aircraft parts, coatings, etc., can solve the problem of not fully meeting the safety requirements of anti-icing on the surface of aircraft

Active Publication Date: 2015-05-13
LIYANG TECH DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the performance of most of the current low surface energy hydrophobic coatings cannot fully meet the safety requirements for anti-icing of aircraft surfaces.

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0020] The propeller blade leading edge assembly according to the present invention comprises a propeller blade leading edge casing and an anti-icing coating located on the outside of the casing, the anti-icing coating includes a primer and a topcoat, the primer is epoxy modified The acrylic primer and topcoat are silicone modified acrylate paints. Preferably, the dry film thickness of the primer and topcoat is 22 microns and 41 microns, respectively. Preferably, the leading edge of the propeller blade referred to in the present invention refers to the front part of the blade projected on the front 1 / 5 range of the chord length. More preferably, the thickness of the anti-icing coating on the leading edge shell is not uniform, for example, gradually becomes thinner from the front end of the blade to the rear, or gradually becomes thicker and then gradually thinner, which can not only improve the anti-icing characteristics but also reduce the Little effect on the aerodynamic pe...

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PUM

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Abstract

A propeller blade leading edge assembly comprises a propeller blade leading edge shell and an anti-icing coat positioned outside the shell, the anti-icing coat comprises a primer and a finish, the primer is an epoxy modified acrylic primer, and the finish is an organosilicon modified acrylate coating; the thicknesses of the dry films of the primer and the finish are 22mum and 41mum respectively; and the organosilicon modified acrylate coating comprises 55-65wt% of an organosilicon modified acrylic resin, 20-25wt% of a color filler, 3wt% of nanometer zinc oxide, 3wt% of nanometer magnesium oxide, 1wt% of a leveling agent, 0.8wt% of an antifoaming agent, 1.2wt% of a dispersant, 0.5wt% of a catalyst and 3-5wt% of a solvent. The propeller blade leading edge assembly made in the invention can effectively reduce the formation of ice layers on the leading edge of a propeller blade and is in favor of the shedding of the formed ice layers.

Description

technical field [0001] The invention relates to a propeller blade leading edge assembly. Background technique [0002] In today's world, airplanes have gradually become a means of transportation that people pay more and more attention to because of their fast and safe features. However, when the aircraft is flying at subsonic speeds below a certain critical Mach number in icing weather conditions, the windward surfaces of some components, such as the leading edge of the propeller blade, will freeze due to the impact and accumulation of water droplets in the atmosphere. A large number of accidents and studies have shown that even a small amount of ice accumulation on key parts of the aircraft will lead to a decrease in the lift of the aircraft and an increase in flight resistance, which will lead to deterioration of the aerodynamic qualities of the aircraft such as maneuverability and stability. Especially when the aero-engine is under a certain temperature and humidity on t...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B32B33/00B32B27/06B64C11/16C09D151/08C09D7/12C08F283/12C08F220/06C08F220/28C08F230/08C08F220/44
Inventor 张俊
Owner LIYANG TECH DEV CENT