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Completed TRL 2 (started at 1, targeting 3)
The demand for higher efficiency gas turbine engines has led to many technical challenges. One of these challenges is managing the temperature of the turbine blades. Typically, engine designers cool these blades using pressurized air which is taken from the main stream and routed through passages inside the blade as well as blown along the surface of the blade in order to keep the blade temperature lower than a given blade temperature limit. Using bleed air has worked well over the years, but through additive manufacturing and innovations in heat transfer technology, it may be unnecessary. Taking air from the main stream leads to a lower air mass flow rate, which resulting in a lower efficiency. One of the most efficient methods for transferring heat is through a pulsating heat pipe (PHP). These devices are used in the electronics industry because of their passive operation and effectiveness at low temperatures. The heat transfer coefficient of these devices can range from 1000-100,000 W/(m2-K). If this technology can be adapted to a gas turbine engine, which operates at extreme temperatures, there would be no need for blade cooling air. An initial concept involves connecting the blades in the turbine sections in a loop using heat pipes, making the blades act as heat sources and sinks resulting in a near-isothermal blade temperature across all stages. The goal of this research and development effort is to increase the thermal efficiency of a high OPR (overall pressure ratio) small core gas turbine by 5% by eliminating the bleed air required for blade cooling.
5-10 years – Eliminate the need for cooling air required for blade cooling in an engine, leading to a more efficient engine while possibly providing an alternative cooling scheme for the implementation of CMC (ceramic matrix composite) blades using a hybrid metallic/CMC design.
10-20 years – Use the technique of ALM with a passive cooling scheme embedded in the structure to produce weight-saving thermal management solutions for any part on an aircraft that can be produced through ALM.
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This is early/mid-stage (TRL 2) — the most realistic path in is NASA SBIR/STTR, which funds small businesses and research institutions to develop technology aligned with NASA's needs (equity-free, phased funding). Check whether a current SBIR/STTR solicitation topic overlaps with this project's technology area, or contact the project directly (above) to ask.
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