Agency: Cordis | Branch: H2020 | Program: RIA | Phase: NMP-01-2014 | Award Amount: 7.68M | Year: 2015
NANOLEAP project aims at the development of a coordinated network of specialized pilot lines for the production of nanocomposite based products for different civil infrastructure and building applications. The goal of this infrastructure is to support the research activities of European SMEs in the Construction sector in nanocomposite products enabling the progress of the product to next steps of technology deployment such as installation of industrial pilot lines and enter in the commercialization stage. For the creation of the NANOLEAP project pilot line network, the most promising applications of polymeric nanocomposites in the construction and engineering sector have been selected. This project will support the pilot lines for the scaling up and production of these nanocomposite based products in order to facilitate their further adoption by the entire construction chain: Antiweathering and anticorrosion nanocomposite coatings for the protection of structures exposed to aggressive environments such as wind turbines, offshore, marine infrastructure. Multifunctional polymeric nanocomposites providing smart applications to traditional construction materials such as concrete and coatings including self-cleaning, hydrophobicity, optical properties, early warning crack and water leak alarm. Prefab non-structural elements such as aerogels mechanically reinforced with nanoparticles for high-thermal insulation applications in building insulation. Coated nanoparticles with improved compatibility with the matrix providing a wide range of functionalities and leading to high quality products and important saves of energy. In order to implement and demonstrate this approach, NANOLEAP project brings together a European Network of pilot production facilities focused on scaling up nanocomposite synthesis and processing methods.
Agency: Cordis | Branch: FP7 | Program: CP-IP | Phase: AAT.2013.1-3. | Award Amount: 45.04M | Year: 2013
The ENOVAL project will provide the next step of engine technologies to achieve and surpass the ACARE 2020 goals on the way towards Flightpath 2050. ENOVAL completes the European 7th Framework Programme (FP7) roadmap of Level 2 aero engine projects. ENOVAL will focus on the low pressure system of ultra-high by-pass ratio propulsion systems (12 < BPR < 20) in conjunction with ultra high overall pressure ratio (50 < OPR < 70) to provide significant reductions in CO2 emissions in terms of fuel burn (-3% to -5%) and engine noise (-1.3 ENPdB). ENOVAL will focus on ducted geared and non-geared turbofan engines, which are amongst the best candidates for the next generation of short/medium range and long range commercial aircraft applications with an entry into service date of 2025 onward. The expected fan diameter increase of 20 to 35% (vs. year 2000 reference engine) is significant and can be accommodated within the limits of a conventional aircraft configuration. It is in line with the roadmap of the Strategic Research and Innovation Agenda for 2020 to have the technologies ready for Optimised conventional aircraft and engines using best fuel efficiency and noise control technologies, where UHBR propulsion systems are expressively named as a key technology. ENOVAL will be established in a consistent series of Level 2 projects in conjunction with LEMCOTEC for core engine technologies, E-BREAK for system technologies for enabling ultra high OPR engines, and OPENAIR for noise reduction technologies. Finally, ENOVAL will prepare the way towards maturing the technology and preparing industrialisation in coordination with past and existing aero-engine initiatives in Europe at FP7 and national levels.
Agency: Cordis | Branch: H2020 | Program: CS2-RIA | Phase: JTI-CS2-2014-CFP01-AIR-02-05 | Award Amount: 588.75K | Year: 2016
NEWCORT will develop and validate novel processes and equipment for the repair of composite airframes. Three key stages in the bonded composite repair procedure were identified, namely material removal & surface preparation, heating for polymerization of patch and positive pressure application for improved compaction of patch layers. In all three stages novel processes will be developed, either through integration of innovations already existing within the proposing consortium or through research focused in targeted areas. For material removal, developments include process optimization to enable close tolerance applications for curved thick composite structures, potentially combined with scarfed pre-cured patches, potential simplification of stepping requirements and adaptation of material removal equipment to most frequent geometries (e.g. fuselage curvature). Novel heating processes and equipment will focus on the polymerization of new types of resins (e.g. M20 at 140oC), possibly including thermoplastic materials, through application of new power supply control logic, dielectric sensors for curing and viscosity monitoring, heating flux sensors for improved curing control, heating mats with embedded thermocouples and dielectric sensors, simulation software for selection of blankets and thermocouples installation topology, as well as development of Quick Composite Repair (QCR) kits for most frequent aircraft repair cases. Finally, the development of positive pressure application equipment for flat / curved structures will be studied, together with optimized pressure measurement devices and control software, mountable to most frequent repair cases (e.g. composite fuselage curvature). The application of such novel processes in real-life aeronautical environment will be guaranteed, through the simultaneous development of all the associated application equipment, resulting in TRL-7 solutions, ready to undergo a full validation campaign during the last project steps.
Agency: Cordis | Branch: FP7 | Program: CP-FP | Phase: AAT.2012.4.1-6. | Award Amount: 2.09M | Year: 2013
The Project aim is to develop and demonstrate an advanced structural surface cooler mounted in an appropriate core fairing composite structure. Currently surface coolers are an integral feature of advanced turbofan engine designs. They contribute to achieving the best engine performance by maintaining oil and fuel temperatures within defined limits and by virtue of their mounting on the inside of the fancase they obviate the need for additional ducting of air and a control valve to switch the air on/off. The lack of ducting and control valve leads to an overall cost and weight reduction. Oil and/or fuel is cooled by the passage of cool engine bypass air flow over the air washed surface of the heat exchanger. Current surface coolers are parasitic to the existing engine structure, and occupy surfaces that can also be used for acoustic treatment to control engine noise. As such the weight, volume and efficiency of the surface cooler are all of great importance. The design and installation of a compact and lightweight structural surface cooler in a core fairing structure will contribute positively to the efficiency of the power-plant by providing the necessary oil cooling at minimum overall weight and hence optimal fuel burn. . Also it is envisaged that surface cooler/composite core fairing designs will evolve that employ novel structural design, advance manufacturing techniques, potentially novel materials and new concepts in utilising air washed surfaces on the engine. The structural integration of the metallic structural surface cooler to a composite core fairing type structure has been identified as an important area for success. The joint must allow a strong load path, handle dissimilar degrees of thermal displacement and provide sealing yet being light and durable. Therefore mounting of such a surface cooler in a composite core fairing structure will also be researched for future engines where composite air washed structures may be used
Agency: Cordis | Branch: FP7 | Program: JTI-CS | Phase: JTI-CS-2011-1-SFWA-02-013 | Award Amount: 90.00K | Year: 2013
This proposal is to design and manufacture an innovative shield to protect critical components of an aircraft against high velocity shrapnel from an engine burst. The concept proposed here exploits the weight advantages of high performance fibres, in a design that uses a net like fibre membrane for energy absorption. Considerations for their integration in an aircraft are made. The proposal has come from a close collaboration between the Imperial College Consultants and Swerea SICOMP. It is therefore the result of the combined skills in manufacturing structural composites for the defence and aeronautical industry as well as specific ballistic design skills. Both institutes have the necessary skills, experience and equipment to design and manufacture a successful shield. As both these institutes are non profit research establishments actively working to advance composite technology, the materials and techniques have been chosen based on the type of treat and the aircraft integration constraints and there is no constrain to use any one particular material supplier. Publishing and dissemination of the results is also not a problem if so desired.