A Study of Creep Characteristics for J-85 Engine Turbine Blade

摘要

The aim of this research work is to guarantee the flight stability of J-85 engine by studying the creep characteristics of turbine blade. Gas turbine engine is operated under the environment of high temperature and pressure, and high centrifugal force. Thus, the durability of the turbine blade continuously operated under this condition become lower because of the creep influence. Creep test is performed to characterize the creep behavior of turbine blade made of Ni-based superalloy (Rene' 80). The test condition is applied for the non-linear stress results considering J-85 engine operating conditions and the fundamental conditions considering material trait. To estimate the non-linear stress with an actual operating condition of J-85 engine, FineTurbo is used to analyze a gas temperature with turbine blade surface and ABAQUS is used to estimate the temperature distribution and stress distribution. Creep curves were fitted using four theta model and the propriety of four theta model is performed to compare between the prediction model and creep test results. It is hard to obtain the creep data with long creep rupture time, theta projection method is used to predict the creep behavior of J-85 engine normal operating condition.