Vacuum plasma erosion resistant 2D nanocomposite coating Avinit for compressor blades of gas turbine engines of aircraft engines

نویسندگان

چکیده

The work is devoted to the search for new vacuum-plasma coatings with high hardness increase durability of compressor blades GTE aircraft engines Ti-Al-N-based obtained by Avinit technologies, which ensure application hard, high-quality dramatically reduced micro-arc damage, were selected as candidates. multilayer have higher functional characteristics than TiN (microhardness, crack resistance, temperature erosion and corrosion resistance) may be promising applying erosion-resistant blades. technologies are technologically closest used in industrial production protective coatings. New multi-layered 2D nanocomposite wear-resistant ion-plasma hard (TiN-AlN)n been developed. created software products made it possible reach a qualitatively level terms further modification improvement designs coatings, stability their quality control when such use gas turbine engines. Special attention paid methods preliminary treatment surfaces before coating. Metallographic studies chemical phase composition structure carried out. thickness 7-9 μm, microhardness 34-35 GPa (compared serially coating: 27.4 GPa). three-stage using double vacuum-arc discharge followed strengthening single technological cycle eliminates formation cracks ensures tightly bonded, given maximally share droplet component. developed applied experimental batches working bench tests.

برای دانلود باید عضویت طلایی داشته باشید

برای دانلود متن کامل این مقاله و بیش از 32 میلیون مقاله دیگر ابتدا ثبت نام کنید

اگر عضو سایت هستید لطفا وارد حساب کاربری خود شوید

منابع مشابه

Isogeometric simulation of turbine blades for aircraft engines

Isogeometric analysis is a novel approach to numerical simulation that has the potential to bridge the gap between geometric design and numerical analysis. It uses the same exact geometry representation in all stages of the product development. In this paper we present recent results which demonstrate the competitiveness of the new concept in an industrial environment, more precisely, in the ch...

متن کامل

Volumetric Geometry Reconstruction of Turbine Blades for Aircraft Engines

We present a framework for generating a trivariate B-spline parametrization of turbine blades from measurement data generated by optical scanners. This new representation replaces the standard patchbased representation of industrial blade designs. In a first step, the blade surface is represented by a smoothly varying family of B-spline curves. In a second step, the blade is parametrized by a t...

متن کامل

Symbolic identification for fault detection in aircraft gas turbine engines

This article presents a robust and computationally inexpensive technique of component-level fault detection in aircraft gas-turbine engines. The underlying algorithm is based on a recently developed statistical pattern recognition tool, symbolic dynamic filtering (SDF), that is built upon symbolization of sensor time series data. Fault detection involves abstraction of a language-theoretic desc...

متن کامل

Fundamentals of the Deep Rolling of Compressor Blades for Turbo Aircraft Engines

The weakening of the fatigue strength of turbine blades due to local impa caused by foreign objects (Foreign Object Damage FOD) represents i3 safety risk in modern aviation. It is possible to employ deep rolling to courat component weakening in a particularly effective way. In order to derive a possible process parameter-set in advance, fundamental knowledge regarding the elastic and plastic de...

متن کامل

ذخیره در منابع من


  با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید

ژورنال

عنوان ژورنال: Mechanics and advanced technologies

سال: 2023

ISSN: ['2522-4255', '2521-1943']

DOI: https://doi.org/10.20535/2521-1943.2023.7.1.264788