BISANCE - BIphasic System integrated in the Airframe of a NaCElle

The project intends to test in icing wind tunnel (IWT) one demonstrator of engine air intake integrated in a nacelle and equipped with an innovative biphasic heat transport system for regenerating the energy from the oil of the engine. The objective, by testing the technology in a representative environment, is to reach TRL5. At the end of the project the technology will be able to be further developed towards TRL6 to 9 with the final aim to be transferred to the aeronautic value chain.

Short Description

Starting point / Motivation

Currently, the ice protection systems (IPS) on turboprop aircrafts are mainly made of inflating boots systems. But for other kinds of aircrafts, ice protection systems can be made of hot bleed air systems or electro thermal systems. These 3 technologies have various limitations and the system investigated in this project, proposed better solutions on the problematic aspects.The perspective of the new heat exchange concept is to optimize the existing system architecture of the aircraft by removing the active cooling system for the oil, removing the active ice protection system, and to harvest the energy from the oil to regenerate it for the ice protection purpose.

Objectives

To demonstrate the possibility to use the energy from the engine oil for protecting the engine air intake against the ice accretion
To optimize the existing system architecture by removing the active cooling system for the oil
To remove the active ice protection system, and to harvest the energy from the oil to regenerate it for the ice protection purpose

Content

The innovation capacity stands in the perspective of replacing the current technologies used for the ice protection systems and for the oil cooling system. The proposed 2-phase system will show various advantages:

Decreasing the gas emissions as being a passive system using waste energy (oil heat) and so with no need of extra energy
Decrease the on-board weight
Limiting the constraints and allowing the engine industry to switch more easily to a bleed less technology

Methodology / Approach

Specification of the bi-phasic system
System design -> conceptual design
System performance calculations -> detailled design
System performance evaluation on a reduced size prototype System performance
Verification on the full size prototype -> reduced size prototype for manufacturing
Final system design -> full size prototype manufacturing
Test of full size prototype manufacturing at RTA Icing Wind Tunnel

Expected results

Reducing the weight of the nacelle/systems by 25kg per Aircraft
Reducing the power consumption of the systems by around 100 kW per Aircraft
To reach TRL5

Project Partners

Sonaca - Coordinator
Calyos SA
RTA Rail Tec Arsenal Fahrzeugversuchsanlage GmbH

Funding program: Clean Sky II