Active Control of Rotor-Lock Noise in Turbofan Engines

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NAS3-02008
Agency Tracking Number: 012575
Amount: $69,896.00
Phase: Phase I
Program: SBIR
Awards Year: 2002
Solicitation Year: N/A
Solicitation Topic Code: N/A
Solicitation Number: N/A
Small Business Information
780 Lakefield Road, Unit G, Westlake Village, CA, 91361
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Bruce Walker
 Principal Investigator
 (805) 373-8533
Business Contact
 Alan Hersh
Title: Vice President
Phone: (805) 373-8533
Research Institution
The proposed innovation is the design of an active control system to reduce aircraft turbofan engine rotor-lock inlet noise generated when rotor tip speeds become transonic. The system design for this program would be tailored to the requirements of the NASA GRC 22-inch diameter Source Diagnostic Fan. The proposed Phase I research program consists of (1) a conceptual design of a prototype active control sound source and (2) a MatLab based design of an active control system. The concept is an innovation because it uses an active/passive segmented liner noise cancellation concept, developed at Hersh Acoustical Engineering, Inc. (HAE) to cancel rotor-lock noise. A successful Phase I research program will establish the feasibility of developing an active control system capable of efficiently suppressing rotor-lock noise.

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

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