Low Mach Scramjet Cavity Flameholder Stabilization, Phase I

This proposal addresses a NASA solicitation topic A2.06 need for propulsion system flow control. A dual mode ram/scram engine is the most likely cycle for the high-speed propulsion flowpath of turbine and rocket based combined cycle engines, but its feasibility with storable liquid hydrocarbon fuels remains to be demonstrated. A key reason is that a stable, low drag engine pilot for the needed operational envelope has eluded us. Due to its simplicity, the cavity flameholder is the subject of renewed investigation, but it suffers from acoustically coupled combustion instabilities originating in the shear flow. Active control of the shear flow over the cavity could substantially improve flameholding stability. Therefore, TDA Research, Inc. (TDA) proposes an active control strategy having no moving parts to manipulate the spectral content and amplitude of shear layer disturbances, and hence control the coupling responsible for resonance and unsteady flow response that leads to premature flame extinguishment. The proposed experimental and analytical development effort will produce a robust, stable and low drag scramjet engine pilot.

This is a mature technology (TRL 7+) — the realistic path in is usually NASA's Technology Transfer Program: licensing an existing NASA patent, or a Space Act Agreement to use NASA facilities/expertise directly. NASA also runs a startup licensing program with no upfront fee for companies formed to commercialize a specific NASA technology.

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