CONTINUUM DYNAMICS INC — Department of Defense STTR Phase I: N22A-T002

Description

To increase efficiency, reduce weight, and improve performance of next-generation aircraft, it is essential to design integrated systems that comprise multiple functionalities.  Modern propulsion systems integrate aircraft engines and air intake diffusers into the airframe to reduce drag.  However, such diffusers often introduce undesirable flow features such as flow separation and distortions, thus reducing the efficiency of propulsion systems.  Continuum Dynamics, Inc., The Pennsylvania State University, and Reaction Engines, Inc. propose to design a multifunctional heat exchanger device in the form of a guide vane cascade that can simultaneously extract swirl and flow distortions for improved engine performance and dissipate a large amount of aircraft waste heat.  This technology will allow for unobtrusive installation and retrofitting into existing engine intake diffusers (e.g., serpentine ducts).  Accordingly, the emphasis of Phase I effort will be on performing numerical simulations, multi-objective optimization processes, and preliminary experimental testing in a simplified flow environment at bench level to demonstrate the feasibility and practicality of the proposed heat exchanger technology.  Phase II will focus on finalizing the design, fabrication, and ground testing of the proposed device to further evaluate heat exchanger effectiveness, pressure loss, and distortion reduction for a representative inlet geometry under various operating conditions.