CRACK INITIATION AND PROPAGATION AROUND HOLES OF Ni-BASED SINGLE CRYSTAL SUPERALLOY DURING THERMAL FATIGUE CYCLE

doi:10.11900/0412.1961.2015.00366

Acta Metall Sin

2015, Vol. 51

Issue (10): 1273-1278 DOI: 10.11900/0412.1961.2015.00366

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CRACK INITIATION AND PROPAGATION AROUND HOLES OF Ni-BASED SINGLE CRYSTAL SUPERALLOY DURING THERMAL FATIGUE CYCLE

Li WANG¹(

),Zhongjiao ZHOU¹,Shaohua ZHANG¹,Xiangdong JIANG²,Langhong LOU¹,Jian ZHANG¹

1 Institute of Metal Research, Chinese Academy of Sciences, Shenyang 110016
2 Beijing Beiye Functional Materials Corporation, Beijing 100192

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Li WANG,Zhongjiao ZHOU,Shaohua ZHANG,Xiangdong JIANG,Langhong LOU,Jian ZHANG. CRACK INITIATION AND PROPAGATION AROUND HOLES OF Ni-BASED SINGLE CRYSTAL SUPERALLOY DURING THERMAL FATIGUE CYCLE. Acta Metall Sin, 2015, 51(10): 1273-1278.

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Abstract

Ni-based single crystal (SX) superalloys are widely used for production of blades in gas turbines and aircraft engines for their superior mechanical performance at high temperatures. To obtain high cooling efficiency, most of the SX blades consist of thin wall with cooling holes. However, thermal fatigue cracks are usually observed in blades with this kind of structures. Thus, it must be valuable to investigate the crack initiation and propagation around a hole during thermal fatigue tests in a SX superalloy. In the present work a second generation SX Ni-based superalloy was used. Plate specimens that parallel to directional solidification (DS) direction and along (100) or (110) planes were prepared. A hole with diameter of 0.5 mm was drilled vertical to the surface in the middle of the plate by electro-discharge machining (EDM). Thermal fatigue tests were performed between room temperature and 1100 ℃. Effect of crystal orientation on the crack initiation and propagation was investigated and the reasons were analyzed. It was found that a thin recast layer was produced around holes of EDM drilled. The thickness of the recast layer was 15 mm in the maximum. Crystal orientation has great effect on the crack initiation sites and propagation kinetics. After 80 cyc thermal fatigue tests, in (110) specimens cracks initiated at the edge of the holes that vertical to the DS direction, then grew quickly and propagated along directions about 45°from the DS direction. After 200 cyc tests, cracks developed to more than 2 mm in length. While in (100) specimens no cracks could be observed even after 200 cyc thermal fatigue tests. This difference was mainly due to the combined effects of different thermal stress caused by the anisotropy of single crystals and of the microstructure characteristics.

Key words: Ni-based single crystal superalloy crystal orientation thermal fatigue hole crack initiation and propagation

Fund: Supported by National Natural Science Foundation of China (No.51201164), National High Technology Research and Development Program of China (No.2012AA03A511) and National Key Scientific Instrument and Equipment Development Project (No.2012YQ22023304)

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	Articles by authors
	Li WANG
	Zhongjiao ZHOU
	Shaohua ZHANG
	Xiangdong JIANG
	Langhong LOU
	Jian ZHANG

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https://www.ams.org.cn/EN/10.11900/0412.1961.2015.00366 OR https://www.ams.org.cn/EN/Y2015/V51/I10/1273

Fig.1 Schematic of Ni-based single crystal superalloy samples for thermal fatigue tests along different crystal planes
(a) (100) specimen (b) (110) specimen

Fig.2 OM image (a) and γ’ morphology (b) of Ni-based single crystal superalloy after full heat treatment

Fig.3 Morphology of hole on (100) specimen (a) and recast layer around the hole (b) of Ni-based single crystal superalloy after electro-discharge machining

Fig.4 Crack growth kinetics curves around holes in (100) and (110) specimens

Fig.5 Morphologies of crack initiation and propagation around holes in (100) specimen (a, c, e) and (110) specimen (b, d, f) after thermal fatigue tests during room temperature to 1100 ℃ for 0 cyc (a, b), 80 cyc (c, d), 120 cyc (e, f) (Inset in Fig.5f shows the macro-morphology)

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