The High Temperature Damage of DV – 2 Turbine Blade Made from Ni – Base Superalloy
High pressure turbine (HPT) blades of DV – 2 jet
engines are made from Ni – based superalloy. This alloy was
originally manufactured in the Soviet Union and referred as ŽS6K.
For improving alloy’s high temperature resistance are blades coated
with Al – Si diffusion layer. A regular operation temperature of HPT
blades vary from 705°C to 750°C depending on jet engine regime.
An overcrossing working temperature range causes degradation of
the protective coating as well as base material which microstructure
is formed by the gamma matrix and strengthening phase gamma
prime (forming small particles in the microstructure). Diffusion
processes inside the material during exposition of the material to high
temperatures causes mainly coarsening of the gamma prime particles,
thus decreasing its strengthening effect. Degradation of the Al – Si
coating caused its thickness growth. All the microstructure changes
and coating layer thickness growth results in decreasing of the turbine
blade operation lifetime.
[1] DV-2-I-62: Company standard, Považské machine industry, Division of
Aircraft Engine DV-2, Považská Bystrica, Slovakia, 1989.
[2] J. Belan, “Structural analyses of advanced materials for aerospace
industry,” Medziagotyra, vol. 14, pp. 315-318, November 2008.
[3] J. Belan, “Study of advanced Ni-base ŽS6K alloy by quantitative
metallography methods,” Manufacturing technology, vol. 13, pp. 2-7,
March 2013.
[4] J. Belan, “Study of advanced materials for aircraft jet engines using
quantitative metallography,” in Recent Advances in Aircraft Technology,
1st ed. Vol. 1, Ramesh K. Agarwal, Ed. Rijeka: InTech, 2012, pp. 49-74.
[5] M. Durand-Chare, The microstructure of superalloys, Gordon & Breach
Science Publishers, Amsterdam, Netherlands, 1997.
[6] C. R. Reed, The superalloys. Fundamentals and applications,
Cambridge University Press, New York, USA, 2006.
[7] Ch. T. Sims, N. S. Stoloff, W. C. Hagel, Superalloys II, 2nd ed. Wiley-
Interscience, USA, 1987. [8] M. J. Donachie, S. J. Donachie, Superalloys – A technical guide, 2nd ed.
ASM International, USA, 2002.
[1] DV-2-I-62: Company standard, Považské machine industry, Division of
Aircraft Engine DV-2, Považská Bystrica, Slovakia, 1989.
[2] J. Belan, “Structural analyses of advanced materials for aerospace
industry,” Medziagotyra, vol. 14, pp. 315-318, November 2008.
[3] J. Belan, “Study of advanced Ni-base ŽS6K alloy by quantitative
metallography methods,” Manufacturing technology, vol. 13, pp. 2-7,
March 2013.
[4] J. Belan, “Study of advanced materials for aircraft jet engines using
quantitative metallography,” in Recent Advances in Aircraft Technology,
1st ed. Vol. 1, Ramesh K. Agarwal, Ed. Rijeka: InTech, 2012, pp. 49-74.
[5] M. Durand-Chare, The microstructure of superalloys, Gordon & Breach
Science Publishers, Amsterdam, Netherlands, 1997.
[6] C. R. Reed, The superalloys. Fundamentals and applications,
Cambridge University Press, New York, USA, 2006.
[7] Ch. T. Sims, N. S. Stoloff, W. C. Hagel, Superalloys II, 2nd ed. Wiley-
Interscience, USA, 1987. [8] M. J. Donachie, S. J. Donachie, Superalloys – A technical guide, 2nd ed.
ASM International, USA, 2002.
@article{"International Journal of Earth, Energy and Environmental Sciences:69880", author = "Juraj Belan and Lenka Hurtalová and Eva Tillová and Alan Vaško and Milan Uhríčik", title = "The High Temperature Damage of DV – 2 Turbine Blade Made from Ni – Base Superalloy", abstract = "High pressure turbine (HPT) blades of DV – 2 jet
engines are made from Ni – based superalloy. This alloy was
originally manufactured in the Soviet Union and referred as ŽS6K.
For improving alloy’s high temperature resistance are blades coated
with Al – Si diffusion layer. A regular operation temperature of HPT
blades vary from 705°C to 750°C depending on jet engine regime.
An overcrossing working temperature range causes degradation of
the protective coating as well as base material which microstructure
is formed by the gamma matrix and strengthening phase gamma
prime (forming small particles in the microstructure). Diffusion
processes inside the material during exposition of the material to high
temperatures causes mainly coarsening of the gamma prime particles,
thus decreasing its strengthening effect. Degradation of the Al – Si
coating caused its thickness growth. All the microstructure changes
and coating layer thickness growth results in decreasing of the turbine
blade operation lifetime.", keywords = "Alitize coating layer, gamma prime phase, high
temperature degradation, Ni – base superalloy ŽS6K, turbine blade.", volume = "9", number = "5", pages = "527-5", }