Investigation on Material's Fatigue Property Variation Among Different Regions of Directional Solidification Turbine Blades—Part I: Fatigue Tests on Full Scale Blades

At present, directional solidification (DS) made blades are commonly used in high performance turbine for their better high temperature mechanical, especially in creep properties compared with the equiaxed grain (EG) blades made by conventional casting method. To predict DS blades' fatigue life accurately, one of the practical ways is to conduct tests on full-scale blades in a laboratory/bench environment. In this investigation, two types of full scale turbine blades, which are made from DZ22B by DS method and K403 by conventional casting method, respectively, were selected to conduct high temperature combined low and high cycle fatigue (CCF) tests on a special design test rig, to evaluate the increase of fatigue life benefitted from material change. Experimental results show that different from EG blades, DS blades' fracture section is not located on the position where the maximum stress point lies. By comparing fatigue test results of the two types of blade, it can be found that the fatigue properties among different regions of the DS blade are different, and its fatigue damage is not only related to the stress field, but also affected by different parts material's fatigue properties.

[1]  Charles Cross Multiaxial testing of gas turbine engine blades , 2000 .

[2]  Liu Zhi-na Numerical Calculation and Measurement of the Vibration Stress in Combined High and Low Cycle Fatigue Tests , 2010 .

[3]  A. Kermanpur,et al.  Simulation of dendritic growth in the platform region of single crystal superalloy turbine blades , 2003 .

[4]  David Nowell,et al.  Prediction of the combined high- and low-cycle fatigue performance of gas turbine blades after foreign object damage , 2007 .

[5]  N. X. Hou,et al.  Application of a combined high and low cycle fatigue life model on life prediction of SC blade , 2009 .

[6]  Markus Rettenmayr,et al.  Simulation of solidification , 1998 .

[7]  Lucjan Witek,et al.  Experimental crack propagation and failure analysis of the first stage compressor blade subjected to vibration , 2009 .

[8]  Nie Jing-xu Inverse method for estimating the vibration stress of turbine blades based on combined high-and-low cycle fatigue tests , 2012 .

[9]  Nie Jing-xu Failure Characteristics of Directional Solidification Turbine Blade Under High Temperature Low Cycle Fatigue Load , 2011 .

[10]  Dianyin Hu,et al.  Combined fatigue experiments on full scale turbine components , 2013 .

[11]  E. Thompson,et al.  Directional structures for advanced aircraft turbine blades , 1976 .

[12]  Steffen Nowotny,et al.  Laser cladding of the titanium alloy TI6242 to restore damaged blades , 2004 .

[13]  Thomas Seifert,et al.  Mechanisms and modelling of fatigue crack growth under combined low and high cycle fatigue loading , 2011 .

[14]  Eberhard Roos,et al.  Numerical and experimental investigations into life assessment of blade–disc connections of gas turbines , 2003 .

[15]  M. Mohammadzadeh,et al.  Directional solidification of Ni base superalloy IN738LC to improve creep properties , 2000 .

[16]  A. Pineau,et al.  Modelling the optimum grain size on the low cycle fatigue life of a Ni based superalloy in the presence of two possible crack initiation sites , 2004 .

[17]  Nagaraj K. Arakere,et al.  Effect of Crystal Orientation on Fatigue Failure of Single Crystal Nickel Base Turbine Blade Superalloys , 2000 .

[18]  Jingxu Nie,et al.  Creep-Fatigue Tests on Full Scale Directionally Solidified Turbine Blades , 2008 .

[20]  M. E. Shank,et al.  The development of columnar grain and single crystal high temperature materials through directional solidification , 1970 .

[21]  Uwe Gampe,et al.  Advanced Experimental and Analytical Investigations on Combined Cycle Fatigue (CCF) of Conventional Cast and Single-Crystal Gas Turbine Blades , 2011 .

[22]  G. Gottstein,et al.  Simulation of primary recrystallization using a modified three-dimensional cellular automaton , 1999 .