New Ni3Al-based directionally-solidified superalloy IC10

Xi Hong Zhao; Zhao Hui Huang; Yong Ning Tan; Qiang Zhang; Qian Yu; Hui Bin Xu

New Ni₃Al-based directionally-solidified superalloy IC10

Xi Hong Zhao^*
, Zhao Hui Huang
, Yong Ning Tan
, Qiang Zhang
, Qian Yu
, Hui Bin Xu

^*Corresponding author for this work

School of Materials Science and Engineering

Beijing Institute of Aeronautical Materials
Beihang University

Research output: Contribution to journal › Article › peer-review

42 Scopus citations

Abstract

A new alloy named as IC10 for aero-engine vane with a service temperature of 1100°C is introduced in this paper. The alloy's composition is characterized by no Ti, 1.5wt% Hf and higher than 19wt% of Al + Ta + Cr. This alloy exhibits superior oxidation resistance and excellent castability. Furthermore, its stress-rupture strength is at the same level with abroad first-generation DS superalloy. The carbides of IC10 alloy is mainly composed of TaC and HfC. Moreover, the formation of M₆C is suppressed by the secondary MC₍₂₎. The incipient melting temperature is increased by elemination of Ni₅Hf through a pre-treatment at 1180°C for 2 h. The low cycle fatigue life of IC10 alloy at 700°C and 980°C was obtained respectively. The thermal-mechanical fatigue test under the condition of 600°C 1100°C was conducted, and the thermal-mechanical fatigue life of IC10 alloy with in-phase and out-of-phase was presented. The aero-engine high-pressure vanes that were made of IC10 alloy is being under PRFT.

Original language	English
Pages (from-to)	20-24
Number of pages	5
Journal	Journal of Aeronautical Materials
Volume	26
Issue number	3
State	Published - Jun 2006

Keywords

Castability
Fatigue
Oxidation
Stress rupture
Superalloy

Cite this

@article{6eb1405e74104e57a0e1f78d1ddfad56,

title = "New Ni3Al-based directionally-solidified superalloy IC10",

abstract = "A new alloy named as IC10 for aero-engine vane with a service temperature of 1100°C is introduced in this paper. The alloy's composition is characterized by no Ti, 1.5wt\% Hf and higher than 19wt\% of Al + Ta + Cr. This alloy exhibits superior oxidation resistance and excellent castability. Furthermore, its stress-rupture strength is at the same level with abroad first-generation DS superalloy. The carbides of IC10 alloy is mainly composed of TaC and HfC. Moreover, the formation of M6C is suppressed by the secondary MC(2). The incipient melting temperature is increased by elemination of Ni5Hf through a pre-treatment at 1180°C for 2 h. The low cycle fatigue life of IC10 alloy at 700°C and 980°C was obtained respectively. The thermal-mechanical fatigue test under the condition of 600°C 1100°C was conducted, and the thermal-mechanical fatigue life of IC10 alloy with in-phase and out-of-phase was presented. The aero-engine high-pressure vanes that were made of IC10 alloy is being under PRFT.",

keywords = "Castability, Fatigue, Oxidation, Stress rupture, Superalloy",

author = "Zhao, \{Xi Hong\} and Huang, \{Zhao Hui\} and Tan, \{Yong Ning\} and Qiang Zhang and Qian Yu and Xu, \{Hui Bin\}",

year = "2006",

month = jun,

language = "英语",

volume = "26",

pages = "20--24",

journal = "Journal of Aeronautical Materials",

issn = "1005-5053",

publisher = "Science Press ",

number = "3",

}

TY - JOUR

T1 - New Ni3Al-based directionally-solidified superalloy IC10

AU - Zhao, Xi Hong

AU - Huang, Zhao Hui

AU - Tan, Yong Ning

AU - Zhang, Qiang

AU - Yu, Qian

AU - Xu, Hui Bin

PY - 2006/6

Y1 - 2006/6

N2 - A new alloy named as IC10 for aero-engine vane with a service temperature of 1100°C is introduced in this paper. The alloy's composition is characterized by no Ti, 1.5wt% Hf and higher than 19wt% of Al + Ta + Cr. This alloy exhibits superior oxidation resistance and excellent castability. Furthermore, its stress-rupture strength is at the same level with abroad first-generation DS superalloy. The carbides of IC10 alloy is mainly composed of TaC and HfC. Moreover, the formation of M6C is suppressed by the secondary MC(2). The incipient melting temperature is increased by elemination of Ni5Hf through a pre-treatment at 1180°C for 2 h. The low cycle fatigue life of IC10 alloy at 700°C and 980°C was obtained respectively. The thermal-mechanical fatigue test under the condition of 600°C 1100°C was conducted, and the thermal-mechanical fatigue life of IC10 alloy with in-phase and out-of-phase was presented. The aero-engine high-pressure vanes that were made of IC10 alloy is being under PRFT.

AB - A new alloy named as IC10 for aero-engine vane with a service temperature of 1100°C is introduced in this paper. The alloy's composition is characterized by no Ti, 1.5wt% Hf and higher than 19wt% of Al + Ta + Cr. This alloy exhibits superior oxidation resistance and excellent castability. Furthermore, its stress-rupture strength is at the same level with abroad first-generation DS superalloy. The carbides of IC10 alloy is mainly composed of TaC and HfC. Moreover, the formation of M6C is suppressed by the secondary MC(2). The incipient melting temperature is increased by elemination of Ni5Hf through a pre-treatment at 1180°C for 2 h. The low cycle fatigue life of IC10 alloy at 700°C and 980°C was obtained respectively. The thermal-mechanical fatigue test under the condition of 600°C 1100°C was conducted, and the thermal-mechanical fatigue life of IC10 alloy with in-phase and out-of-phase was presented. The aero-engine high-pressure vanes that were made of IC10 alloy is being under PRFT.

KW - Castability

KW - Fatigue

KW - Oxidation

KW - Stress rupture

KW - Superalloy

UR - https://www.scopus.com/pages/publications/33746260186

M3 - 文章

AN - SCOPUS:33746260186

SN - 1005-5053

VL - 26

SP - 20

EP - 24

JO - Journal of Aeronautical Materials

JF - Journal of Aeronautical Materials

IS - 3

ER -

New Ni₃Al-based directionally-solidified superalloy IC10

Abstract

Keywords

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