Aero Engine Integration of Heat Exchangers

Purpose and goal

The project "aero engine INTEgration of Heat EXchangers", INTEHEX, aims to develop and test compact and efficient geometries to integrate megawatt class heat exchangers in civilian and military aircraft engines. An inverse design method will be developped to provide near-optimal geometries for the ducting into and from the heat exchangers, which will reduce pressure loss and volume and weight of the target engine.

Expected effects and result

The project will develop design methods for flow channels that can be used in future research projects for energy-efficient engines with heat exchangers that preheat cryogenic fuels, cool electrical systems, intercool compressor air, evaporate water for injection into the combustor or condense water from exhaust gases. By providing more optimal designs this will give guidance to which technical innovations are realistic for the next generation of engines.

Planned approach and implementation

The project will study three aspects of heat exchanger integration in aircraft engines. 1) To quantify how heat exchangers affect the flow in the inlet duct to it. 2.) To theoretically and experimentally investigate passive and active systems to avoid instabilities during the velocity reduction in the flow duct. 3) To investigate the performance and flow stability of innovative engine configurations for commercial and military applications.