Tool for Blade Stress Estimation during Multiple Simultaneous Vibratory Mode Responses

Award Information
Agency:
Department of Defense
Amount:
$99,274.00
Program:
STTR
Contract:
FA9550-12-C-0047
Solitcitation Year:
2011
Solicitation Number:
2011.B
Branch:
Air Force
Award Year:
2012
Phase:
Phase I
Agency Tracking Number:
F11B-T22-0116
Solicitation Topic Code:
AF11-BT22
Small Business Information
NextGen Aeronautics
2780 Skypark Drive, Suite 400, Torrance, CA, -
Hubzone Owned:
N
Woman Owned:
N
Socially and Economically Disadvantaged:
Y
Duns:
106823607
Principal Investigator
 Adarsh Pun
 Principal Investigator
 (310) 626-8653
 apun@nextgenaero.com
Business Contact
 Zoltan Feher
Title: Manager, Contracts and Pricing
Phone: (310) 626-8384
Email: zfeher@nextgenaero.com
Research Institution
 San Diego State University
 Eugene Stein
 5500 Campanile Drive
San Diego, CA, 92182-2182
 (619) 594-8731
 Nonprofit college or university
Abstract
ABSTRACT: NextGen Aeronautics, leveraging past experience in generating stress spectra from static and vibratory loads as well as knowledge of gas turbines, is proposing a method for estimating blade stresses from multiple vibratory loads in rotating systems in Phase I. Additionally, we will develop and easy-to-use software application to integrate stresses from multiple modes using a super-positioning principle. We will demonstrate technology on generic integrally bladed turbines and leverage commercial-of-the-shelf tools for modal analysis and use the modal stresses together with a forcing function to sum up stresses on discrete or all locations on a blade. Our team consists of experts in dynamics and vibration and has strong support from P & W for the technology transition phase. BENEFIT: The technology finally developed in this program will directly benefit safe operation of gas turbines in the aviation industry as well as industrial steam and wind turbines, through better estimation of stresses generated from multiple vibratory loads. Costly re-designs from pre-mature failures in ground and flight test programs will be avoided and will aid in intelligent inspection intervals for safe operation of rotating systems.

* information listed above is at the time of submission.

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