High Temperature Smart Structures for Engine Noise Reduction and Performance Enhancement

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNC06CA03C
Agency Tracking Number: 040779
Amount: $599,832.00
Phase: Phase II
Program: SBIR
Awards Year: 2006
Solicitation Year: 2004
Solicitation Topic Code: A2.03
Solicitation Number: N/A
Small Business Information
34 Lexington Avenue, Ewing, NJ, 08618-2302
DUNS: 096854313
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Todd Quackenbush
 Principal Investigator
 (609) 538-0444
 todd@continuum-dynamics.com
Business Contact
 Barbara Agans
Title: Business Official
Phone: (609) 538-0444
Email: barbara@continuum-dynamics.com
Research Institution
N/A
Abstract
Noise mitigation for subsonic transports is a continuing high priority, and recent work has identified successful exhaust mixing enhancement devices (chevrons) that have demonstrated substantial capability for reducing aircraft engine noise in critical takeoff and landing conditions. Existing fixed-geometry chevrons, however, are inherently limited to optimal noise mitigation in a single operating condition and also can impose significant performance penalties in cruise flight. An adaptive geometry chevron using embedded smart structures technology offers the possibility of maximizing engine performance while retaining and possibly enhancing the favorable noise characteristics of current designs. Phase I identified a promising candidate for a variable geometry chevron using high force Shape Memory Alloy (SMA) actuators. Building on coupled CFD/finite element modeling predicting successful performance, subscale demonstration-level actuated chevrons were constructed that yielded the required deflections in both benchtop and low speed wind tunnel tests. Phase I also identified and tested new high temperature SMA (HTSMA) materials technology to enable the devices to operate in both low temperature (fan) and high temperature (core) exhaust flows. The proposed Phase II effort will continue development of this technology and demonstrate extension of this concept to operation at full-scale stiffness levels and at realistic dynamic pressure and temperature conditions.

* Information listed above is at the time of submission. *

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