Abstract
Problems of increasing the service life of compressor blades of aircraft gas turbine engines using detonation spraying technology are considered. The simulation of the parameters of the velocity and temperature of the particles of the sprayed material in the barrel of the detonation unit and in the flooded space to the substrate was carried out, followed by the choice of the optimal technological parameters of the spraying process. The control system of the detonation unit has been modernized. An experiment was carried out on the deposition of the Al2O3 coatings on the samples of a substrate made of titanium alloy VT3-1. Based on the results of the experiment, technological recommendations were developed concerning both the parameters of the spraying process and the parameters of the preparation of the substrate surface before spraying. The equipment for brazing the blades of the guide vanes is described and a device for spraying coatings on the end surfaces of the compressor blades is proposed. Thus, a complex technology has been developed for restoring the end surfaces of titanium alloy compressor blades by deposition of Al2O3 coatings.
Highlights
Modern aircraft engines are a scientific and high-tech product, which has no analogs in terms of stress level and thermal condition of parts among other engineering products
The analysis of two-phase flows is carried out under the following assumptions: the pressure is created by gas only, the influence of particles is neglected; solid particles that are spheres of the same radius, -spaced between the sections X1 and X2 in the barrel and interact with each other and the barrel’s walls, the particles are inert and do not interact with the products of detonation; there is no mass transfer between gas and powder; the volume occupied by the particles can be neglected; due to the high thermal conductivity of the particles’ material, their temperature in the entire volume is constant; gravitational and electric forces can be neglected (Davidson, 2015)
The manufacturability of the device is provided by the modularity, as well as the possibility of adjustment and control, which ensured the compactness of the device compared to the previous version
Summary
Modern aircraft engines are a scientific and high-tech product, which has no analogs in terms of stress level and thermal condition of parts among other engineering products. Among the above-mentioned parts, the most numerous, complex in configuration and variety of used materials are compressor and turbine blades, their manufacturing process presupposes the use of all types of metalworking, followed by finishing and strengthening (IDC Technologies, 2013). It should be noted the peculiarities of engines’ operating conditions installed on helicop-. Research aimed at the modernization and development of equipment, recommendations for the implementation of innovative technological processes for repair, restoration geometry, since the quality and durability of aircraft engines parts are relevant
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