NASA SBIR 2018-I Solicitation

Proposal Summary

 18-1- A1.02-2313
 Quiet Performance - Propulsion Noise Reduction Technology
 Prediction and Modal Analysis of Supersonic Jet Noise From Complex Nozzles in an Integrated Simulation Environment
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
CASCADE Technologies, Inc.
2445 Faber Place, Suite 100
Palo Alto , CA 94303-3346
(650) 521-0243

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)
Guillaume Bres
2445 Faber Place, Suite 100 Palo Alto, CA 94303 - 3346
(650) 521-0243

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)
Guillaume Bres
2445 Faber Place, Suite 100 Palo Alto, CA 94303 - 3346
(650) 521-0243
Estimated Technology Readiness Level (TRL) :
Begin: 6
End: 7
Technical Abstract

Our long-term vision is to seamlessly integrate resolvent operator-based spectral analysis into Cascade’s high-fidelity large eddy simulation (LES) environment, for accurate prediction and efficient modeling of supersonic jet noise from complex nozzles. Resolvent analysis is a frequency-domain technique that can identify resonance phenomena such as jet screech and other tonal acoustic effects, predict the large-scale coherent structures that are the main source of aft angle jet noise, and that provides, at the same time, sensitivity maps that can be used for optimal sensor or actuator placement for noise control. Cascade’s LES framework features a novel mesh generation paradigm based on the computation of Voronoi diagrams, which allows for the generation of high-quality, body-fitted, conformal meshes and the use of low-dissipation numerical methods required for high fidelity large eddy simulations of multi-scale turbulent flows in complex geometries. We project that the combination of the Voronoi-based LES and resolvent analysis can be successfully commercialized by assuming a role similar to that of modal analysis in solid mechanics. In Phase I, we propose the case of a heated supersonic over-expanded turbulent jet issuing from a circular convergent-divergent nozzle as a testbed for both Cascade’s Voronoi-based LES framework and a resolvent analysis tool provided by Caltech as a subcontractor. The first task is to implement and validate shock-capturing capabilities into both the resolvent tool and LES compressible flow solver “Charles”. Armed with the large-eddy simulation data, The second task is to conducte a detailed resolvent analysis of the over-expanded turbulent jet, with special emphasis on broadband aft angle and tonal shock-induced noise. In parallel, the final task is to perform a proof-of-concept simulation for an airframe-integrated nozzle, as a demonstration of the meshing and prediction capabilities for complex geometries.

Potential NASA Applications

The supersonic over-expanded turbulent jet test case proposed as a testbed for our numerical method mimics the take-off operation conditions of supersonic commercial aircraft such as NASA’s Quiet Supersonic Transport design. Other technologies that potentially benefit from resonance mechanism identification include the chemical thrusters and rocket boosters used by NASA's Orion spacecraft and Space Launch System.

Potential Non-NASA Applications

Jet noise and flow-induced vibrations affect the surrounding structures and flight deck crew on aircraft carriers. Our envisioned simulation and analysis tools are therefore ideally suited to guide the aeroacoustical design and optimization of Naval aviation programs. Similarly, passive noise mitigation measures used in the commercial aviation sector such as chevrons can benefit from our developments.

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