Effect Of Technological Parameters Of Production Of Tfp Preforms Of Gas Turbine Engine Blades On Their Physical And Mechanical Properties

Orlov Maksim Andreyevich Et Al

doi:10.17762/turcomat.v12i5.730

Abstract

The article discusses the features of the destruction of carbon fiber reinforced plastics on the basis of tfp-preforms produced using various stitching mode parameters, and provides for studies of their physical and mechanical properties and structure. The effect of the carbon fiber laying density and the piercing step of the aramid yarn on the elastic-strength properties of composites is shown. The optimal technological parameters for creating tfp-preforms of gas turbine engine blades were chosen.

Highlights

Carbon fiber reinforced plastics (CFRP), the preforms of which are obtained by the tailored fiber placement (TFP) technology [1, 2], represent a promising class of materials with a complex of unique properties[3, 4]
The machine automatically moves the carrier material in accordance with a software template developed for produced TFP preforms.in the manufacture of such materials, due to the penetration of the needle of the sewing machine, defects are formed in the reinforcing structure, which can significantly reduce the elastic-strength characteristics of reinforced plastics
It can be seen that the destruction of the sewn samples (Figure 1a-1d) is localized in the central area. This type of cracking is typical for carbon fiber reinforced plastics that break when bent from normal stresses

Summary

Introduction

Carbon fiber reinforced plastics (CFRP), the preforms of which are obtained by the tailored fiber placement (TFP) technology [1, 2], represent a promising class of materials with a complex of unique properties[3, 4]. To achieve optimal elastic-strength properties, the technological preform stitching parameters (roving laying density ρand the piercing step Δ) that are currently poorly studied should be taken into account. This is important for high strength parts, for example, for gas turbine engine blades (GTE blades)

Methods

Results

Conclusion