Development of directionally solidified Ni-Al-Mo-B-Y alloy IC6A

C. B. Xiao; Y. F. Han; S. S. Li; J. X. Song

doi:10.1179/026708303225008194

Development of directionally solidified Ni-Al-Mo-B-Y alloy IC6A

C. B. Xiao^*
, Y. F. Han
, S. S. Li
, J. X. Song

^*Corresponding author for this work

Research institute of Aero-Engine

Beijing Institute of Aeronautical Materials

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

2 Scopus citations

Abstract

A directionally solidified Ni₃Al based alloy designated IC6A with the chemical composition Ni-(7·5-8·5)Al-(13· 0-15·0)Mo-(0·02-0·1)B-(0·001-0·20)Y (wt-%) has been recently developed as a high-temperature structural material for advanced jet-engine vanes operating in the. temperature range 1050-1100°C Microstructural analysis results show that the regions consisted of Ni ₃Y, Mo_1.24Ni_0.76 and γ phases and surrounded by large size γ' phases precipitate in the interdendritic areas of alloy IC6A when the content of yttrium is near to the upper limit. Ni₃Y and Mo_1.24Ni_0.76 have no obvious change during high temperature aging. A needle like or rod like phase named Y - NiMo precipitates after aging at 950°C for about 200 h. The high temperature cyclic oxidation resistance of alloy IC6A is fairly good owing to the presence of yttrium. The tensile properties, high temperature stress rupture properties and creep properties, high cycle fatigue properties and impact toughness of alloy IC6A were investigated to meet the needs of aeroengine turbine vanes.

Original language	English
Pages (from-to)	1677-1680
Number of pages	4
Journal	Materials Science and Technology (United Kingdom)
Volume	19
Issue number	12
DOIs	https://doi.org/10.1179/026708303225008194
State	Published - Dec 2003

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title = "Development of directionally solidified Ni-Al-Mo-B-Y alloy IC6A",

abstract = "A directionally solidified Ni3Al based alloy designated IC6A with the chemical composition Ni-(7·5-8·5)Al-(13· 0-15·0)Mo-(0·02-0·1)B-(0·001-0·20)Y (wt-\%) has been recently developed as a high-temperature structural material for advanced jet-engine vanes operating in the. temperature range 1050-1100°C Microstructural analysis results show that the regions consisted of Ni 3Y, Mo1.24Ni0.76 and γ phases and surrounded by large size γ' phases precipitate in the interdendritic areas of alloy IC6A when the content of yttrium is near to the upper limit. Ni3Y and Mo1.24Ni0.76 have no obvious change during high temperature aging. A needle like or rod like phase named Y - NiMo precipitates after aging at 950°C for about 200 h. The high temperature cyclic oxidation resistance of alloy IC6A is fairly good owing to the presence of yttrium. The tensile properties, high temperature stress rupture properties and creep properties, high cycle fatigue properties and impact toughness of alloy IC6A were investigated to meet the needs of aeroengine turbine vanes.",

author = "Xiao, \{C. B.\} and Han, \{Y. F.\} and Li, \{S. S.\} and Song, \{J. X.\}",

year = "2003",

month = dec,

doi = "10.1179/026708303225008194",

language = "英语",

volume = "19",

pages = "1677--1680",

journal = "Materials Science and Technology (United Kingdom)",

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TY - JOUR

T1 - Development of directionally solidified Ni-Al-Mo-B-Y alloy IC6A

AU - Xiao, C. B.

AU - Han, Y. F.

AU - Li, S. S.

AU - Song, J. X.

PY - 2003/12

Y1 - 2003/12

N2 - A directionally solidified Ni3Al based alloy designated IC6A with the chemical composition Ni-(7·5-8·5)Al-(13· 0-15·0)Mo-(0·02-0·1)B-(0·001-0·20)Y (wt-%) has been recently developed as a high-temperature structural material for advanced jet-engine vanes operating in the. temperature range 1050-1100°C Microstructural analysis results show that the regions consisted of Ni 3Y, Mo1.24Ni0.76 and γ phases and surrounded by large size γ' phases precipitate in the interdendritic areas of alloy IC6A when the content of yttrium is near to the upper limit. Ni3Y and Mo1.24Ni0.76 have no obvious change during high temperature aging. A needle like or rod like phase named Y - NiMo precipitates after aging at 950°C for about 200 h. The high temperature cyclic oxidation resistance of alloy IC6A is fairly good owing to the presence of yttrium. The tensile properties, high temperature stress rupture properties and creep properties, high cycle fatigue properties and impact toughness of alloy IC6A were investigated to meet the needs of aeroengine turbine vanes.

AB - A directionally solidified Ni3Al based alloy designated IC6A with the chemical composition Ni-(7·5-8·5)Al-(13· 0-15·0)Mo-(0·02-0·1)B-(0·001-0·20)Y (wt-%) has been recently developed as a high-temperature structural material for advanced jet-engine vanes operating in the. temperature range 1050-1100°C Microstructural analysis results show that the regions consisted of Ni 3Y, Mo1.24Ni0.76 and γ phases and surrounded by large size γ' phases precipitate in the interdendritic areas of alloy IC6A when the content of yttrium is near to the upper limit. Ni3Y and Mo1.24Ni0.76 have no obvious change during high temperature aging. A needle like or rod like phase named Y - NiMo precipitates after aging at 950°C for about 200 h. The high temperature cyclic oxidation resistance of alloy IC6A is fairly good owing to the presence of yttrium. The tensile properties, high temperature stress rupture properties and creep properties, high cycle fatigue properties and impact toughness of alloy IC6A were investigated to meet the needs of aeroengine turbine vanes.

UR - https://www.scopus.com/pages/publications/0347595737

U2 - 10.1179/026708303225008194

DO - 10.1179/026708303225008194

M3 - 文章

AN - SCOPUS:0347595737

SN - 0267-0836

VL - 19

SP - 1677

EP - 1680

JO - Materials Science and Technology (United Kingdom)

JF - Materials Science and Technology (United Kingdom)

IS - 12

ER -

Development of directionally solidified Ni-Al-Mo-B-Y alloy IC6A

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