Response of an Operational Turbofan Engine to a Simulated Nuclear Blast

[+] Author and Article Information
M. G. Dunn, C. Padova

Physical Sciences Department, Calspan Advanced Technology Center, Buffalo, N.Y.

R. M. Adams

Headquarters/SPAS, Defense Nuclear Agency, Alexandria, Va.

J. Fluids Eng 109(2), 121-129 (Jun 01, 1987) (9 pages) doi:10.1115/1.3242631 History: Received August 26, 1986; Online October 26, 2009


This paper describes the results of a measurement program designed to determine the transient response of an air-breathing propulsion system to simulated nuclear blast waves. A Ludwieg-tube facility, incorporating a driver technique consisting of an activating chamber and a nonfrangible diaphragm, was used to create the required shock waves. Detailed measurements were performed at incident shock overpressures of approximately 6.9, 10.3, 13.8, and 17.2 kPa (1.0, 1.5, 2.0, and 2.5 psi). For each of these overpressures, data were obtained for engine speeds of 0, 80, 90, and 100 percent of maximum speed. Typical results are presented for distortion patterns at the fan face for both an extended bellmouth and a S-shaped inlet at either 0 or 20 deg yaw angle.

Copyright © 1987 by ASME
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