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2016 | OriginalPaper | Buchkapitel

Aero-Structure Interaction for Mechanical Integration of HP Compressor Blades in a Gas Engine Rotor

verfasst von : N. Vinayaka, Nilotpal Banerjee, B. S. Ajay Kumar, Kumar K. Gowda

Erschienen in: CAD/CAM, Robotics and Factories of the Future

Verlag: Springer India

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Abstract

Aero-structure interaction during turbomachinery blade design has become an important area of research due to its critical applications in aero engines, land based gas turbines. Studies reveal that a small mistuning leads to stress build up through mode localization under operating conditions. This paper deals with a case study of Aero-structure interaction for a free standing HP blade of a gas turbine. Assuming 100 % fixity at blade root, the study involves critical parametric evaluations involved in achieving Mechanical Integrity in airfoil design and blade platform design. Mechanical Integrity involves stress checks, frequency margins, Campbell diagram, gross yield stress and so on, for design and off-design conditions for a given stage efficiency of 72 % in an Ideal HP compressor of a gas turbine engine.

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Literatur
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Zurück zum Zitat Bazhenov, V. A., Gulyar, A. I., Piskunov, S. O., & Andrievskii, V. P. (2013). Design life assessment of the blade root of a gas turbine unit under thermo mechanical loading. Journal of Strength of Materials, 45(3), 329–339.CrossRef Bazhenov, V. A., Gulyar, A. I., Piskunov, S. O., & Andrievskii, V. P. (2013). Design life assessment of the blade root of a gas turbine unit under thermo mechanical loading. Journal of Strength of Materials, 45(3), 329–339.CrossRef
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Metadaten
Titel
Aero-Structure Interaction for Mechanical Integration of HP Compressor Blades in a Gas Engine Rotor
verfasst von
N. Vinayaka
Nilotpal Banerjee
B. S. Ajay Kumar
Kumar K. Gowda
Copyright-Jahr
2016
Verlag
Springer India
DOI
https://doi.org/10.1007/978-81-322-2740-3_78

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