Requirements for reliability and safety of modern aircraft engines are constantly growing [1–2]. Among these requirements is periodic inspection of the engine condition and condition of its individual parts during operation, for the purpose of evaluation of the risk to operation. This is to ascertain possible damage to various engine parts in the course of operation and progressive wear. Damage can occur for a variety of reasons: ingestion of foreign matter in the engine gas path, operation in extreme and off-design conditions, wear, etc. To trace the engine parts condition and detect various damage on the engine parts, periodic inspection is provided. In case of any damage or deviations on parts, the question of their performance and possibility to break during operation are addressed. There are two ways of answering this question:
1 – experimental demonstration of the required strength of parts with damage;
2 – computational demonstration of the required strength of parts with damage.
The first way requires a good deal of time and money for carrying out the experiments. It is efficient only with enough operational experience in typical parts with various surface damage. While developing a new engine (having no prototypes) it is more reasonable to use computational methods.
To determine the allowable damage of gas-turbine engine parts, a special procedure has been developed. Its main principles consist of the following:
- classification of the typical parts damage by foreign object ingestion;
- determination of the stress concentration factors (Kt) due to damage for various defect sizes;
- determination of strength factors of safety and life for various zones of parts without damage;
- determination of Kt values with which minimum allowable values of strength safety factor and life are attained;
- determination of allowable sizes of various types of damage for all zones of each part based on previously defined Kt dependencies on typical damage sizes.
This methodology is proposed for determination of allowable damage on the surface of gas-turbine engines stator parts caused by foreign object ingestion in order to ensure the required reliability and safety; its experimental verification is foreseen for the future.
Effect of welding parameters on microstructure and tensile properties of CA-TIG welded AMS-5596 grade thin high temperature alloy sheets for gas turbine engine applications
