The tool developed will also be useful to a number of industries, including gas turbine manufacturers for civilian energy and aviation applications. The tool will also be useful to the Air Force in the design of propulsion devices such as the engine for the Joint Strike Fighter. The software developed in this SBIR will allow cost-effective design and analysis of combustion systems. The ability to avoid combustion-driven instability and investigation of high-payoff ideas will be possible. The final product will be marketable to OEMs and designers/manufacturers of gas turbines, I.C. engines and other combustion/propulsion devices which can be affected by combustion instability. The tool will also be useful in missile propulsion system designs such as X-51, Waverider as well as Standard Missile 6 upgrades. It will also be useful in the next generation launch vehicles such as Falcon.
The model developed in this SBIR project will be extremely useful in identifying the potential sources of combustion instability, and ways to suppress them. The tools developed will allow mitigation of instability problems in the design-phase, eliminating expensive testing needed when combustion instabilities occur in engine testing. The methods developed under this project will have wide ranging applications at NASA, including design of propulsion devices such as solid rocket motors, liquid rocket engines and gas turbine combustors important in the design of the Heavy Lift Launch System, In-space propulsion systems, numerous planetary spacecraft missions, etc. The instability analysis methodology developed in this SBIR project can also be applied to high-speed combustion devices such as ramjet and scramjet engines, as the method combines the key advantages of both sufficiently detailed CFD analysis and accurate system-level modeling paradigm. In this respect, the tool will be useful to NASA's Hypersonics Program.
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