Acoustic Test Method for Turbofan Engine Exhaust Systems at Cruise Conditions

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$572,250.00
Award Year:
2004
Program:
SBIR
Phase:
Phase II
Contract:
NNC04CB20C
Agency Tracking Number:
022268
Solicitation Year:
2002
Solicitation Topic Code:
A2.01
Solicitation Number:
n/a
Small Business Information
Aero Systems Engineering, Inc.
358 East Fillmore Avenue, St. Paul, MN, 55107-1289
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
041776824
Principal Investigator:
Dean Long
Principal Investigator
(651) 220-1290
dlong@aerosysengr.com
Business Contact:
Steven Hedberg
CFO and Treasurer
(651) 220-1222
shedberg@aerosysengr.com
Research Institution:
n/a
Abstract
The exhaust flow from a turbofan engine operating at typical cruise conditions generates noise as turbulent flow interacts with the basic shock cell pattern. This can be a significant source of noise within the aircraft cabin. The proposed innovation is a new method for testing the acoustics of model scale turbofan engine exhaust systems at cruise conditions in a transonic wind tunnel. This would complement the aerodynamic tests now conducted in the wind tunnel. Currently, acoustic data at cruise conditions is only obtained from costly flight tests. Wind tunnel tests are desirable to simulate the proper flight conditions, but acoustic measurements are difficult in this environment. The new method involves three specific areas of innovation: a) phased-array noise measurement methods, b) evaluating potential modifications to an existing wind tunnel, and c) evaluating means for reducing model air supply noise. Phase I demonstrated that each of these problems has been solved. The proposed Phase II research will combine these processes into an efficient measurement procedure. It will lead to a successful commercial service to airframe manufacturers faced with meeting recently enacted legislation governing noise in the aircraft cabin.

* information listed above is at the time of submission.

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