A reduction in the temperature of available cooling air would provide additional heat sink, thereby enabling use of higher combustion temperatures. The benefits of such a concept include reduced fuel burn and the accompanying reduction in CO2 emissions, in alignment with NASA's goals, with accompanying minimal fire risk. This technology would be applicable to any NASA air-breathing fuel-based propulsion systems where available cooling air temperatures are currently too high to reach the desired performance goals.
The ability to provide cooled cooling air with minimal fire risk offers a compelling value proposition to turbine manufacturers and their clients. A major engine manufacturer has interest in incorporating the proposed concept into future civil and defense gas turbine engine products that currently show benefits from fuel-cooled cooling air. The designs proposed are inherently compatible with Micro Cooling Concepts' existing production line, enabling arrangements such as building the components under contract or licensing the IP to the engine manufacturer and/or their suppliers.