High-Fidelity Simulation of Turbofan Noise

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$99,975.00
Award Year:
2009
Program:
SBIR
Phase:
Phase I
Contract:
NNX09CC83P
Award Id:
90583
Agency Tracking Number:
084195
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
P. O. Box 3001, Champaign, IL, 61826
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
792045713
Principal Investigator:
MarkBrandyberry
Principal Investigator
(217) 766-2567
mdbrandy@illinoisrocstar.com
Business Contact:
WilliamDick
Business Official
(217) 417-0885
wdick@illinoisrocstar.com
Research Institute:
n/a
Abstract
Broadband fan noise ýý closely tied to turbulent flow on and around the fan blades ýý represents a key challenge to the noise reduction community due to the interaction of a highly turbulent flow field with complex, moving geometries. Prediction and high-fidelity simulation of fan noise demands a fundamental innovation in CFD methods due to moving geometries and accuracy requirements. The objective this work is to develop a flexible approach to handling multiple, overset grids for use in simulations of turbomachinery. In Phase 1 we will develop an innovative computational software tool for efficiently managing multiple, overlapping structured meshes in relative motion. This application will be used concurrently with a compressible Navier-Stokes solver and is an enabling technology in enabling high-fidelity simulations of turbulent flows in complex, moving geometries. Phase 1 will demonstrate software feasibility using a simplified model of the NASA Glenn Source Diagnostic Test (SDT) fan at realistic take-off conditions. We propose a simulation that includes a moving "rotor" blade row adjacent to a static blade row. Tailored post-processing of simulation results will provide information on the turbulent flow ýý and implied turbulent noise sources ýý including unsteady blade surface pressures, acoustic modes, and overall radiated noise. In Phase 2 we focus primarily on broadband turbulent noise sources of modern turbofan engines. By utilizing a realistic NASA SDT fan geometry and take-off flow conditions, we will use our new tools to simulate real-world systems and commercialize our software product.

* information listed above is at the time of submission.

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