Material Selection for High Pressure (HP) Turbine Blade of Conventional Turbojet Engines

Ikpe Aniekan Essienubong; Owunna Ikechukwu; Patrick. O. Ebunilo; Ememobong Ikpe

doi:doi:10.11648/j.ajmie.20160101.11

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Material Selection for High Pressure (HP) Turbine Blade of Conventional Turbojet Engines

Ikpe Aniekan Essienubong, Owunna Ikechukwu, Patrick. O. Ebunilo, Ememobong Ikpe

Published in American Journal of Mechanical and Industrial Engineering (Volume 1, Issue 1)

Received: 5 June 2016 Accepted: 13 June 2016 Published: 23 June 2016

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Abstract

Turbojet engine can be divided into three major sections including the compressor, combustion chamber and the gas turbine section. The relatively high temperature gas that passes through the high pressure turbine stages of a turbojet engine from the combustion chamber has a direct effect on the performance and efficiency of the gas turbine, which may hamper its longevity in the long run, particularly the turbine blades. The turbine blades extract energy from the high temperature gas and transfer the kinetic energy of the flowing gas to the compressor stages where it provides forward thrust and rotates the turbine shaft which drives the high pressure and low Pressure compressor fan blades. However, the ability of materials to withstand this high temperature is based on properties of such materials which can be attributed to advances in material selection, improvement techniques in terms of surface protection and cooling as well as manufacturing processes which this paper is based on. Material indices were derived for High Pressure (HP) turbine blades to determine materials that can resist yielding and creep condition when exposed to high temperature above 700°C in a turbojet engine gas turbine. Based on the material indices derived, CES software 2014 was used to generate graphs showing materials with adequate fracture toughness, fatigue strength, stiffness and yield strength property that can withstand the in-service condition of HP turbine blade. Considering all these properties in terms of relatively high temperature, Nickel based super alloys dominated the graphs but in terms of density, titanium alloys dominated as CES software gave the minimum density of nickel alloy (8150 kg/m³) as twice that of titanium alloy (4410 kg/m³). Although both alloys are very expensive, nickel based alloy particularly Nickel-Cr-Co-Mo Super alloy also known as Rene 41 was chosen because of its excellent corrosion property and high strength at elevated temperature (About 1000°C) which makes it suitable for conventional HP turbine blade application.

Published in	American Journal of Mechanical and Industrial Engineering (Volume 1, Issue 1)
DOI	10.11648/j.ajmie.20160101.11
Page(s)	1-9
Creative Commons	This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited.
Copyright	Copyright © The Author(s), 2024. Published by Science Publishing Group

Keywords

Temperature, Failure, HP Turbine Blades, Cyclic Stresses, High Strength, Low Density, Turbojet Engine

References

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[9]	Eckardt, D. and Rufli, P. (2002) Advanced Gas Turbine Technology. ABB/BBC Historical Firsts. ASME J. Eng Gas Turbine Power pp 124, 542-549
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[17]	Nathan, S. (2015) Jewel in the Crown: Rolls-Royce’s Single-Crystal Turbine Blade Casting Foundry. [online] available [2 August 2015]
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[19]	Princeton University (2000) Oxidation of a polycrystalline titanium surface by oxygen and water [online] available from [10 March 2014]
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APA Style

Ikpe Aniekan Essienubong, Owunna Ikechukwu, Patrick. O. Ebunilo, Ememobong Ikpe. (2016). Material Selection for High Pressure (HP) Turbine Blade of Conventional Turbojet Engines. American Journal of Mechanical and Industrial Engineering, 1(1), 1-9. https://doi.org/10.11648/j.ajmie.20160101.11

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ACS Style

Ikpe Aniekan Essienubong; Owunna Ikechukwu; Patrick. O. Ebunilo; Ememobong Ikpe. Material Selection for High Pressure (HP) Turbine Blade of Conventional Turbojet Engines. Am. J. Mech. Ind. Eng. 2016, 1(1), 1-9. doi: 10.11648/j.ajmie.20160101.11

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AMA Style

Ikpe Aniekan Essienubong, Owunna Ikechukwu, Patrick. O. Ebunilo, Ememobong Ikpe. Material Selection for High Pressure (HP) Turbine Blade of Conventional Turbojet Engines. Am J Mech Ind Eng. 2016;1(1):1-9. doi: 10.11648/j.ajmie.20160101.11

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@article{10.11648/j.ajmie.20160101.11,
  author = {Ikpe Aniekan Essienubong and Owunna Ikechukwu and Patrick. O. Ebunilo and Ememobong Ikpe},
  title = {Material Selection for High Pressure (HP) Turbine Blade of Conventional Turbojet Engines},
  journal = {American Journal of Mechanical and Industrial Engineering},
  volume = {1},
  number = {1},
  pages = {1-9},
  doi = {10.11648/j.ajmie.20160101.11},
  url = {https://doi.org/10.11648/j.ajmie.20160101.11},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ajmie.20160101.11},
  abstract = {Turbojet engine can be divided into three major sections including the compressor, combustion chamber and the gas turbine section. The relatively high temperature gas that passes through the high pressure turbine stages of a turbojet engine from the combustion chamber has a direct effect on the performance and efficiency of the gas turbine, which may hamper its longevity in the long run, particularly the turbine blades. The turbine blades extract energy from the high temperature gas and transfer the kinetic energy of the flowing gas to the compressor stages where it provides forward thrust and rotates the turbine shaft which drives the high pressure and low Pressure compressor fan blades. However, the ability of materials to withstand this high temperature is based on properties of such materials which can be attributed to advances in material selection, improvement techniques in terms of surface protection and cooling as well as manufacturing processes which this paper is based on. Material indices were derived for High Pressure (HP) turbine blades to determine materials that can resist yielding and creep condition when exposed to high temperature above 700°C in a turbojet engine gas turbine. Based on the material indices derived, CES software 2014 was used to generate graphs showing materials with adequate fracture toughness, fatigue strength, stiffness and yield strength property that can withstand the in-service condition of HP turbine blade. Considering all these properties in terms of relatively high temperature, Nickel based super alloys dominated the graphs but in terms of density, titanium alloys dominated as CES software gave the minimum density of nickel alloy (8150 kg/m3) as twice that of titanium alloy (4410 kg/m3). Although both alloys are very expensive, nickel based alloy particularly Nickel-Cr-Co-Mo Super alloy also known as Rene 41 was chosen because of its excellent corrosion property and high strength at elevated temperature (About 1000°C) which makes it suitable for conventional HP turbine blade application.},
 year = {2016}
}

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TY  - JOUR
T1  - Material Selection for High Pressure (HP) Turbine Blade of Conventional Turbojet Engines
AU  - Ikpe Aniekan Essienubong
AU  - Owunna Ikechukwu
AU  - Patrick. O. Ebunilo
AU  - Ememobong Ikpe
Y1  - 2016/06/23
PY  - 2016
N1  - https://doi.org/10.11648/j.ajmie.20160101.11
DO  - 10.11648/j.ajmie.20160101.11
T2  - American Journal of Mechanical and Industrial Engineering
JF  - American Journal of Mechanical and Industrial Engineering
JO  - American Journal of Mechanical and Industrial Engineering
SP  - 1
EP  - 9
PB  - Science Publishing Group
SN  - 2575-6060
UR  - https://doi.org/10.11648/j.ajmie.20160101.11
AB  - Turbojet engine can be divided into three major sections including the compressor, combustion chamber and the gas turbine section. The relatively high temperature gas that passes through the high pressure turbine stages of a turbojet engine from the combustion chamber has a direct effect on the performance and efficiency of the gas turbine, which may hamper its longevity in the long run, particularly the turbine blades. The turbine blades extract energy from the high temperature gas and transfer the kinetic energy of the flowing gas to the compressor stages where it provides forward thrust and rotates the turbine shaft which drives the high pressure and low Pressure compressor fan blades. However, the ability of materials to withstand this high temperature is based on properties of such materials which can be attributed to advances in material selection, improvement techniques in terms of surface protection and cooling as well as manufacturing processes which this paper is based on. Material indices were derived for High Pressure (HP) turbine blades to determine materials that can resist yielding and creep condition when exposed to high temperature above 700°C in a turbojet engine gas turbine. Based on the material indices derived, CES software 2014 was used to generate graphs showing materials with adequate fracture toughness, fatigue strength, stiffness and yield strength property that can withstand the in-service condition of HP turbine blade. Considering all these properties in terms of relatively high temperature, Nickel based super alloys dominated the graphs but in terms of density, titanium alloys dominated as CES software gave the minimum density of nickel alloy (8150 kg/m3) as twice that of titanium alloy (4410 kg/m3). Although both alloys are very expensive, nickel based alloy particularly Nickel-Cr-Co-Mo Super alloy also known as Rene 41 was chosen because of its excellent corrosion property and high strength at elevated temperature (About 1000°C) which makes it suitable for conventional HP turbine blade application.
VL  - 1
IS  - 1
ER  -

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Author Information

Ikpe Aniekan Essienubong

Department of Mechanical Engineering, Coventry University, West Midlands, UK
Owunna Ikechukwu

Department of Mechanical Engineering, Coventry University, West Midlands, UK
Patrick. O. Ebunilo

Department of Mechanical Engineering, University of Benin, Benin City, Nigeria
Ememobong Ikpe

Department of Instrumentation and Control, Exxon Mobil Producing Nigeria, Akwa Ibom State, Nigeria

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APA Style

Ikpe Aniekan Essienubong, Owunna Ikechukwu, Patrick. O. Ebunilo, Ememobong Ikpe. (2016). Material Selection for High Pressure (HP) Turbine Blade of Conventional Turbojet Engines. American Journal of Mechanical and Industrial Engineering, 1(1), 1-9. https://doi.org/10.11648/j.ajmie.20160101.11

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ACS Style

Ikpe Aniekan Essienubong; Owunna Ikechukwu; Patrick. O. Ebunilo; Ememobong Ikpe. Material Selection for High Pressure (HP) Turbine Blade of Conventional Turbojet Engines. Am. J. Mech. Ind. Eng. 2016, 1(1), 1-9. doi: 10.11648/j.ajmie.20160101.11

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AMA Style

Ikpe Aniekan Essienubong, Owunna Ikechukwu, Patrick. O. Ebunilo, Ememobong Ikpe. Material Selection for High Pressure (HP) Turbine Blade of Conventional Turbojet Engines. Am J Mech Ind Eng. 2016;1(1):1-9. doi: 10.11648/j.ajmie.20160101.11

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@article{10.11648/j.ajmie.20160101.11,
  author = {Ikpe Aniekan Essienubong and Owunna Ikechukwu and Patrick. O. Ebunilo and Ememobong Ikpe},
  title = {Material Selection for High Pressure (HP) Turbine Blade of Conventional Turbojet Engines},
  journal = {American Journal of Mechanical and Industrial Engineering},
  volume = {1},
  number = {1},
  pages = {1-9},
  doi = {10.11648/j.ajmie.20160101.11},
  url = {https://doi.org/10.11648/j.ajmie.20160101.11},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ajmie.20160101.11},
  abstract = {Turbojet engine can be divided into three major sections including the compressor, combustion chamber and the gas turbine section. The relatively high temperature gas that passes through the high pressure turbine stages of a turbojet engine from the combustion chamber has a direct effect on the performance and efficiency of the gas turbine, which may hamper its longevity in the long run, particularly the turbine blades. The turbine blades extract energy from the high temperature gas and transfer the kinetic energy of the flowing gas to the compressor stages where it provides forward thrust and rotates the turbine shaft which drives the high pressure and low Pressure compressor fan blades. However, the ability of materials to withstand this high temperature is based on properties of such materials which can be attributed to advances in material selection, improvement techniques in terms of surface protection and cooling as well as manufacturing processes which this paper is based on. Material indices were derived for High Pressure (HP) turbine blades to determine materials that can resist yielding and creep condition when exposed to high temperature above 700°C in a turbojet engine gas turbine. Based on the material indices derived, CES software 2014 was used to generate graphs showing materials with adequate fracture toughness, fatigue strength, stiffness and yield strength property that can withstand the in-service condition of HP turbine blade. Considering all these properties in terms of relatively high temperature, Nickel based super alloys dominated the graphs but in terms of density, titanium alloys dominated as CES software gave the minimum density of nickel alloy (8150 kg/m3) as twice that of titanium alloy (4410 kg/m3). Although both alloys are very expensive, nickel based alloy particularly Nickel-Cr-Co-Mo Super alloy also known as Rene 41 was chosen because of its excellent corrosion property and high strength at elevated temperature (About 1000°C) which makes it suitable for conventional HP turbine blade application.},
 year = {2016}
}

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TY  - JOUR
T1  - Material Selection for High Pressure (HP) Turbine Blade of Conventional Turbojet Engines
AU  - Ikpe Aniekan Essienubong
AU  - Owunna Ikechukwu
AU  - Patrick. O. Ebunilo
AU  - Ememobong Ikpe
Y1  - 2016/06/23
PY  - 2016
N1  - https://doi.org/10.11648/j.ajmie.20160101.11
DO  - 10.11648/j.ajmie.20160101.11
T2  - American Journal of Mechanical and Industrial Engineering
JF  - American Journal of Mechanical and Industrial Engineering
JO  - American Journal of Mechanical and Industrial Engineering
SP  - 1
EP  - 9
PB  - Science Publishing Group
SN  - 2575-6060
UR  - https://doi.org/10.11648/j.ajmie.20160101.11
AB  - Turbojet engine can be divided into three major sections including the compressor, combustion chamber and the gas turbine section. The relatively high temperature gas that passes through the high pressure turbine stages of a turbojet engine from the combustion chamber has a direct effect on the performance and efficiency of the gas turbine, which may hamper its longevity in the long run, particularly the turbine blades. The turbine blades extract energy from the high temperature gas and transfer the kinetic energy of the flowing gas to the compressor stages where it provides forward thrust and rotates the turbine shaft which drives the high pressure and low Pressure compressor fan blades. However, the ability of materials to withstand this high temperature is based on properties of such materials which can be attributed to advances in material selection, improvement techniques in terms of surface protection and cooling as well as manufacturing processes which this paper is based on. Material indices were derived for High Pressure (HP) turbine blades to determine materials that can resist yielding and creep condition when exposed to high temperature above 700°C in a turbojet engine gas turbine. Based on the material indices derived, CES software 2014 was used to generate graphs showing materials with adequate fracture toughness, fatigue strength, stiffness and yield strength property that can withstand the in-service condition of HP turbine blade. Considering all these properties in terms of relatively high temperature, Nickel based super alloys dominated the graphs but in terms of density, titanium alloys dominated as CES software gave the minimum density of nickel alloy (8150 kg/m3) as twice that of titanium alloy (4410 kg/m3). Although both alloys are very expensive, nickel based alloy particularly Nickel-Cr-Co-Mo Super alloy also known as Rene 41 was chosen because of its excellent corrosion property and high strength at elevated temperature (About 1000°C) which makes it suitable for conventional HP turbine blade application.
VL  - 1
IS  - 1
ER  -

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