Engine Infra-Red (IR) Signature Suppression

The objective of this project is to develop a lightweight, low drag IR (infra-red light spectrum) suppression system for SOF aircraft. Power, weight and aircraft performance are negatively effected by traditinal suppression concepts and therefore, a new approach to the design problem is required. The proposed design effort will explore a unique design solution to reduce weight and aircraft drag. A complaint flexible seal between the turbine's aft flange and the suppressor duct provides reduced vibration load in the suppressor so material thickness can be reduced. The cooling process utilized in this design is a combination of high level of exhaust plume dilution by ejection of ambient air, cooling of exposed parts, and shielding of hot turbine parts. Advanced high temperature composite materials are currently available that are 30% lighter than traditional turbine exhaust materials. The drag impacts are minimizd by a high aspect ratio duct with close fairing to the engine nacelle. Analysis will be conduted to establish the performance of the design as well as the estimated weight and drag impacts. The applicability of such a lightweight suppression system will be evaluated for the following SOF aircraft: C-130, H-47D, H-53D, H-60, and the MV-X.