Abstract
The material selection method is critically evaluated to enable high pressure (HP) turbine blades to deal with in-service damaging phenomena such as creep, low cycle fatigue and high cycle fatigue, oxidation and corrosion. The material selection method is analyzed in order to improve the service life of the aero engine. To increase the turbine inlet temperature, HP turbine blades need improved creep and fatigue resistance. more quality. By the typical working condition of HP turbine blade, using CES Edu Pack (CES) material selection software was used to select suitable materials for HP turbine blade material. Nickel based alloys are selected for HP turbine blades, such as Nickel-Cr-Co-Mo superalloy.
Highlights
The aeroengine is a highly complex and precise thermodynamic machine
Every important change in the history of human aviation is related to the technological progress of aero engines
After more than a hundred years of development, aeroengine have developed into mature products with extremely high reliability
Summary
The aeroengine is a highly complex and precise thermodynamic machine. As the heart of the aircraft, it is the driving force for aircraft flight and an important driving force for the development of aviation. Every important change in the history of human aviation is related to the technological progress of aero engines. The high pressure (HP) turbine is one of the important components of the aviation gas turbine engine. In order to obtain high performance with small size and lightweight, the main measure is to adopt higher combustion gas turbine inlet temperatures (TIT).
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