SBIR-STTR Award

Several high-fidelity computational schemes and turbulence-combustion interaction models, including the option for high-order spatial and temporal calculations, are proposed to significantly improve the accuracy and turnaround time for practical scramjet engine design and performance analysis. The proposed enhancements of existing tools, such as the government-owned VULCAN computer program, focus on accuracy, speed of execution, and general user interaction with the tools. The project targets issues associated with physics-based modeling of supersonic combustion, aerodynamics, turbulence, and their interactions, with the overall goal of providing accurate and computationally affordable tool. To develop the proposed software, TTC Technologies, Inc. (TTC) is leveraging its extensive experience in the relevant research for the topic and in developing truly advanced computational fluid dynamics (CFD) solutions at all speeds (subsonic, transonic, supersonic, and hypersonic). TTC will also partner with ATK GASL, Inc., who will provide quality data to validate the proposed tool, and leverage its extensive research and realistic scramjet manufacturing experience.

Keywords:
Scramjet, High-Fidelity Computational Fluid Dynamics, Hybrid Rans/Les, Flamelet-Based Turbulent Combustion Model, Multi-Phase Flow, Droplet Breakup And Evaporation

Several high-fidelity computational schemes and turbulence-combustion interaction models, including the option for high-order spatial and temporal calculations, are proposed to significantly improve the accuracy and turnaround time for practical scramjet engine design and performance analysis. The proposed enhancements of existing tools, such as the government-owned VULCAN computer program, focus on accuracy, speed of execution, and general user interaction with the tools. The project targets issues associated with physics-based modeling of supersonic combustion, aerodynamics, turbulence, and their interactions, with the overall goal of providing accurate and computationally affordable tool. To develop the proposed software, TTC Technologies, Inc. (TTC) is leveraging its extensive experience in the relevant research for the topic and in developing truly advanced computational fluid dynamics (CFD) solutions at all speeds (subsonic, transonic, supersonic, and hypersonic). TTC will also partner with ATK GASL, Inc., who will provide quality dataset to validate the proposed tool, and leverage its extensive research and realistic scramjet manufacturing experience.

Benefit:
Supersonic combustion is a vital, application-driven field of research, occurring in supersonic ramjets (scramjets) and rocket engine devices. The extreme operating conditions of these applications, such as Mach 4 through 7 for scramjets, and ambient vacuum, for rocket engine ignition, make ground-based experimental measurements very expensive and difficult. The use of computational fluid dynamics (CFD) could potentially play a vital role as an important complement or a substitute for experiments. Therefore, TTC''''s proposed high fidelity scramjet combustion software will add significant value to realistic scramjet design and performance analysis, with high accuracy and fast turnaround time. Moreover, the nature of the proposed software is such that its marketing synergizes with that of TTCs other software products, including its flagship CFD tool, AEROFLO. Both government and private sectors will find the proposed software to be very valuable.  DOD and the National Aeronautics and Space Administration (NASA) will find it beneficial for their various projects on hypersonic air vehicle concept screening. The expected accuracy and robustness of the procedure also assures reduced time, risk and cost for commercial development of hypersonic propulsion capability for access to space using hydrocarbon fuels. The software modules could be licensed or sold to providers of analysis tools.

Keywords:
Scramjet, High-Fidelity Computational Fluid Dynamics, Hybrid Rans/Les, Flamelet-Based Turbulent Combustion Model, Multi-Phase Flow, Droplet Breakup An