High-Fidelity Simulation of Turbofan Noise

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX09CC83P
Agency Tracking Number: 084195
Amount: $99,975.00
Phase: Phase I
Program: SBIR
Awards Year: 2009
Solicitation Year: 2008
Solicitation Topic Code: A2.03
Solicitation Number: N/A
Small Business Information
P. O. Box 3001, Champaign, IL, 61826-3001
DUNS: 792045713
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Mark Brandyberry
 Principal Investigator
 (217) 766-2567
 mdbrandy@illinoisrocstar.com
Business Contact
 William Dick
Title: Business Official
Phone: (217) 417-0885
Email: wdick@illinoisrocstar.com
Research Institution
N/A
Abstract
Broadband fan noise — closely tied to turbulent flow on and around the fan blades — 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 — and implied turbulent noise sources — 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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