Stress of a Rocket Turbine under Different Loads Using Finite Element Modeling

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Turbopump unit is a key component of the liquid rocket engine assembly and in this paper stresses of a turbopump turbine are investigated using finite element (FE) analysis. Three-dimensional solid modeling of a group of blades and a sector of the disc was first created on CAD software and subsequently exported to a FE package for analysis. The FE results reveals that the maximum stresses in the blades result from rotational and thermal loads owing to the relatively high operating speed and temperature of the turbine and they are located at the root of the blades. Also, the maximum stresses in the disc result from rotational and thermal loads, but with higher values than those in the blades and they are located at the center of the disc. The result of this study may serve as a guideline in the selection of the materials for both the disc and blades.

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Periodical:

Edited by:

Amanda Wu

Pages:

691-696

Citation:

E. Amr and G. Z. Liang, "Stress of a Rocket Turbine under Different Loads Using Finite Element Modeling", Applied Mechanics and Materials, Vol. 232, pp. 691-696, 2012

Online since:

November 2012

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$38.00

[1] S. H. YOON, S. M. J., AND J. KIM. Transient Thermal and Structural Analysis of the Liquid Rocket Turbopump Turbine. ASME Summer Heat Transfer Conference. San Francisco, California, USA (2005).

DOI: https://doi.org/10.1115/ht2005-72070

[2] Poursaeidi, E., m. Aieneravaie and m. r. mohammadi. Failure analysis of a second stage blade in a gas turbine engine. Engineering Failure Analysis, 15 (2008) 1111-1129.

DOI: https://doi.org/10.1016/j.engfailanal.2007.11.020

[3] GOWREESH, S., N.S. REDDY AND N.V. MURTHY. Convective heat transfer analysis of an aero-gas turbine blade using ANSYS. International Journal of Mechanics and Solids, 4 (2009) 55-62.

[4] Abdul-aziz, Ali. Assessment of crack growth in a space shuttle main engine first-stage high-pressure fuel turbopump blade. Finite Elements in Analysis and Design, 39 (2002) 1-15.

DOI: https://doi.org/10.1016/s0168-874x(02)00058-6

[5] Sayyah, m.T. and W.P. Schonberg. New failure criterion for space shuttle main engine turbine blades. Journal of Spacecraft and Rockets, 39 (2002) 140-145.

DOI: https://doi.org/10.2514/2.3792

[6] arakere, n. k. and g. swanson. Effect of crystal orientation on fatigue failure of single crystal nickel base turbine blade superalloys. Journal of Engineering for Gas Turbines and Power, 124(2002) 161-176.

DOI: https://doi.org/10.1115/1.1413767

[7] Witek, l. Failure Analysis of turbine disc of an aero engine. Engineering Failure Analysis, 13(2006) 9-17.

DOI: https://doi.org/10.1016/j.engfailanal.2004.12.028

[8] jeon, s. m. and j. kim. Investigation on the strength and vibration safety of the liquid rocket turbopump. International Astronautical Federation , 5 (2005) 3386-3391.

[9] Clark, Claude L., High temperature alloys, Material Engineer Special st., (1993).