Thermomechanical fatigue failure investigation on a single crystal nickel superalloy turbine blade

Abstract

A thermomechanical fatigue (TMF) test rig was developed consisting of the loading, heating, synchronizing, cooling and monitoring systems. Moreover, the specimen was particularly designed to provide adequate load-bearing capability at the blade tip in order to simulate the actual turbine blade loads in laboratory. TMF test on a single crystal nickel superalloy turbine blade was conducted. Then the specimen was segmented in a novel way to preserve the crack surface to investigate the TMF mechanism of the turbine blade. Visual examination together with the metallographic analysis indicated that the most severe TMF damage occurred at the pin-fin fillet on the suction side near the trailing edge. Furthermore, finite element simulation results were compared to the experiment, in which a viscoplastic constitutive model was employed.

Damage‐based low‐cycle fatigue lifetime prediction of nickel‐based single‐crystal superalloy considering anisotropy and dwell types

“…Therefore, there are 30 slip systems which are possible to active during the deformation process of nickel‐based single‐crystal superalloys. However, in general, the activation condition of the octahedral secondary slip system is relatively complicated, and it is a common practice to consider 12 octahedral primary slip systems <110> {111} and six cube slip systems <110> {100} during the establishing of the constitutive model and lifetime prediction model 9,13,30–32 . The octahedral primary slip systems <110> {111} and cube slip systems <110> {100} are shown in Figures 1 and 2, respectively.…”

Mechanical Fatigue Testing Under Thermal Gradient and Manufacturing Variabilities in Nickel-Based Superalloy Parts with Air-Cooling Holes

“…It looks like loadings often encountered with Thermal Fatigue where specimens aren't free to deform as seen in the MAATRE test rig [11,12]. Many works in the literature can be found concerning such kind of testings as the selection of new materials for aeronautical applications [13] or the study of real HPTB geometries [14,15]. More precisely on the damaging around cooling holes as the effect of trepanning speed laser drilling [16], through the skew angle [17] and mechanical response [18,19].…”

Research on Parametric Model for Surface Processing Prediction of Aero-Engine Blades

“…Since the 1960s, the large-scale industrialization of aviation products has led to the development of engine blade manufacturing technology, which in turn has improved the overall performance of aircraft engines. Since the compressor blades and turbine blades of the engine are made of difficult-to-machine materials, casting and forging techniques are applied more frequently during the machining process [1][2]. Fig.…”