Introduction to Aero Engine Blades

The degradation mechanisms for environmental barrier coatings (EBCs) under high-temperature water vapour conditions are vital for the service of aero-engine blades.

With the development of advanced aviation engines in the direction of high thrust-to-weight ratio and lightweight, a series of lightweight aviation materials such as titanium alloys, nickel-based high-temperature alloys, and ceramic-based composite materials have emerged and been widely used for the key components in the aerospace field, and have also become the main production materials for aero-engine blades.

In this study, the aero-engine blades processed by abrasive belt grinding and the vibration fatigue test bench were used to explore the influence of surface roughness, surface texture, and surface residual stress on the fatigue performance of aero-engine blades under actual working conditions.

Aero-engine blades often fracture failed due to resonance.

In addition to blade inspection, other applications such as repair and adaptive machining of aero-engine blades can equally benefit from the proposed method for automatic airfoil profile reconstruction.

This article summarizes the fatigue fracture problems of aero-engine blades, provides a systematic basic theory for the design, innovation and development of aero-engine blades, and has certain reference value.

The high performance of aero-engines requires light-weight aero-engine blades, so hollow structures have been widely used in aero-engine blades.

The complexity of aero-engine blades deformation after multi-axis milling causes poor consistency in batch blades.

Aero-engine blades are manufactured by electroforming process with electrodes.

Abrasive belt flap wheel has large elastic deformation, which can better fit the surface of aero-engine blades.

Remanufacturing technique has been widely used for repairing the damaged regions of aero-engine blades.

As precision machining process of aero-engine blades, the surface integrity after abrasive belt grinding closely related to its fatigue resistance.

High cycle fatigue failure has been recognized as one of the major forms of failure of aero-engine blades.

Thirdly, the mass moments of a group of aero-engine blades were weighed using a moment scale (MW0), and the blade mass moment distribution and assembly unbalance under the six blade arrangements were analyzed.

Residual stress during the machining process has always been a research hotspot, especially for aero-engine blades.

Aero-engine blades are an integral part of the aero-engine, and the integrity of these blades affects the flight performance and safety performance of an aircraft.

This method is suitable for the sampling measurement and compression of the data of blades, aircraft wings, and other similar free-form surfaces, and is especially suitable for solving the inefficiency problem caused by repeated measurements made in the process of iterative machining of aero-engine blades.

Nickel-based superalloys are a diverse group of materials commonly used for components such as aero engine blades, guides and the cartridge receiver in the hot sections of gas and steam turbines.

The demand of improving the accuracy of leading/trailing edges of aero engine blades has increased continually.