Coupled Pyrolysis, Radiant Heat Transfer, and Fluid Dynamics Modeling

Award Information
Agency:
Department of Defense
Branch:
Army
Amount:
$990,315.00
Award Year:
2012
Program:
SBIR
Phase:
Phase II
Contract:
W31P4Q-13-C-0044
Agency Tracking Number:
A2-5048
Solicitation Year:
2011
Solicitation Topic Code:
A11-075
Solicitation Number:
2011.2
Small Business Information
Combustion Research and Flow Technology,
6210 Kellers Church Road, Pipersville, PA, -
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
929950012
Principal Investigator
 Brian York
 Principal Scientist
 (215) 766-1520
 york@craft-tech.com
Business Contact
 Neeraj Sinha
Title: Vice President&Technica
Phone: (215) 766-1520
Email: sinha@craft-tech.com
Research Institution
 Stub
Abstract
The Phase II effort will unify advanced models for simulating post burn out effects in solid rocket motors (SRM"s), coupling fluid dynamic, radiative, and conductive heat transfer processes using innovative parallelization strategies. Complex processes such as surface pyrolysis and slag formation/buildup/breakup will be modeled. Models will be integrated into a Navier Stokes CFD code that itself contains very advanced multi-phase/combustive capabilities. Previously developed high-fidelity radiative and conduction heat transfer models will serve as starting points for this effort with Phase II work extending them to analyze a rocket motor environment. Since these models operate on different grids than our CFD code, coupling requires significant attention and innovation in view of the different scales. In Phase I, we focused on coupling the fluid dynamics with a radiative heat transfer model, and we accounted for the radiative absorption and scattering by the hot gases and particles in the chamber, in a very preliminary manner. We demonstrated this for a simplified rocket chamber flow. In Phase II, we will implement motor specific submodels (for pyrolysis, etc.), develop an"end-to-end"SRM model that can analyze post burn out events for varied flight scenarios, and analyze such scenarios for a real motor.

* information listed above is at the time of submission.

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