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The ATAAC project aims at improvements to Computational Fluid Dynamics (CFD) methods for aerodynamic flows used in today's aeronautical industry. The accuracy of these is limited by insufficient capabilities of the turbulence modelling / simulation approaches available, especially at the high Reynolds numbers typical of real-life flows. As LES will not be affordable for such flows in the next 4 decades, ATAAC focuses on approaches below the LES level, namely Differential Reynolds Stress Models (DRSM), advanced Unsteady RANS models (URANS), including Scale-Adaptive Simulation (SAS), Wall-Modelled LES, and different hybrid RANS-LES coupling schemes, including the latest versions of DES and Embedded LES. The resources of the project will be concentrated exclusively on flows for which the current models fail to provide sufficient accuracy, e.g. in stalled flows, high lift applications, swirling flows (delta wings, trailing vortices), buffet etc. The assessment and improvement process will follow thoroughly conceived roadmaps linking practical goals with corresponding industrial application challenges and with modelling/simulation issues through stepping stones represented by appropriate generic test cases. The final goals of ATAAC are: - to recommend one or at most two best DRSM for conventional RANS and URANS- to provide a small set of hybrid RANS-LES and SAS methods that can be used as reference turbulence-resolving approaches in future CFD design tools - to formulate clear indications of areas of applicability and uncertainty of the proposed approaches for aerodynamic applications in industrial CFD - Contributing to reliable industrial CFD tools, ATAAC will have a direct impact on the predictive capabilities in design and optimisation, and directly contribute to the development of Greener Aircraft.
Since the publication of the ACARE goals, the commercial and political pressure to reduce CO2 has increased considerably. DREAM is the response of the aero-engine community to this pressure. The first major DREAM objective is to design, integrate and validate new engine concepts based on open rotor contra-rotating architectures to reduce fuel consumption and CO2 emissions 7Prozent beyond the ACARE 2020 objectives. Open rotors are noisier than equivalent high bypass ratio turbofan engines, therefore it is necessary to provide solutions that will meet noise ICAO certification standards. The second major DREAM objective is a 3dB noise emission reduction per operation point for the engine alone compared to the Year 2000 engine reference. These breakthroughs will be achieved by designing and rig testing: Innovative engine concepts a geared and a direct drive contra-rotating open rotor (unducted propulsion system) Enabling architectures with novel active and passive engine systems to reduce vibrations These technologies will support the development of future open rotor engines but also more traditional ducted turbofan engines. DREAM will also develop specifications for alternative fuels for aero-engines and then characterise, assess and test several potential fuels. This will be followed by a demonstration that the selected fuels can be used in aero-engines. The DREAM technologies will then be integrated and the engine concepts together with alternative fuels usage assessed through an enhanced version of the TERA tool developed in VITAL and NEWAC. DREAM is led by Rolls-Royce and is made of 47 partners from 13 countries, providing the best expertise and capability from the EU aeronautics industry and Russia. DREAM will mature technologies that offer the potential to go beyond the ACARE objectives for SFC, achieving a TRL of 4-5. These technologies are candidates to be brought to a higher TRL level within the scope of the CLEAN SKY JTI. Prime Contractor: Rolls Royce PLC; London; United Kingdom.
In a modern aero engine, up to 20Prozent of the main annulus flow is bled off to perform cooling and sealing functions. The vicinity of these bleed ports and flow sinks is characterised by complex unsteady swirling flows, which are not fully understood. Even the most up-to-date numerical tools have difficulties predicting the behaviour of the secondary flow system when interacting with the main annulus. The project addresses interactions between main gas path and secondary flow systems in commercial gas turbines in response to Research Activity AERO-2005-1.3.1.2a Concepts and technologies for improving engine thermal efficiency and reducing secondary air losses. Experiments are planned on turbine disc rim and compressor manifold cavity heat transfer, hot gas ingestion, and spoiling effects of cooling air flow and their impact on turbine and compressor performance, as well as a reduction of secondary air losses. The experimental data will be used for better understanding of the complex flow phenomena and improvements of platform and cavity design. Furthermore, the industrial partners will validate their design tools with these test data and improve their prediction capability of secondary flow systems when interacting with the main gas path. The expected results are a reduction of cooling and sealing airflow rates, improvements of the turbine and compressor efficiency and increase of the safety margin of the engine components by better cooling. Expected technical results are: - Knowledge of the interaction phenomena and its effect on cavity heat transfer, spoiling and performance, - Experimental results for validation of improved numerical tools for secondary flow systems, - Optimised design methods and CFD best practice guidelines. The targeted outcome will contribute to the ACARE goal of reduced CO2 emissions via reduced fuel burn of 2Prozent to improve the environment and strengthening the competitiveness of European gas turbine manufacturers.
General Information: The aim of the research proposal is to obtain an on-line process control of liquid gas and water atomization using extended Phase-Doppler-Anemometry(PDA). This will lead to higher quality of the powders and PM-products and an improvement of the production efficiency by the minimization of rejected material. This aim will be reached by fulfilling the following tasks: - Construction and installation of a laboratory measurement system to determine particle velocity, size and concentration seperately for particles of different materials using extended PDA. - Development of a prototype spraying system with integrated PDA - Atomization tests for the evaluation of the parameters. - Modelling of liquid gas and water atomization to obtain data for the development of a closed control loop for the optimization of powders. - Set-up of a closed control-loop in the atomization units and verification. Fulfilling these tasks, it will be possible to realize an on-line control of the melt spraying process, especially for liquid gas and water atomization, where, in some parts of the spray systems, liquid gas or water and molten metal drops will be present simultaneously. This requires a measurement technique, not only for droplet size, velocity and concentration, but also to distinguish between droplet material and atomizing medium (by determining the refractive index of the dispersed phase). The most appropriate measurement technique for this is extended PDA. Achievements: The main aim of the research work has been reached by the development of a process control system for melt atomization. Within reasonable accuracy limits, on-line PDA is able to predict the entire powder size by a single point measurement. Some restriction, such as the applicability of EPDA to LGA only for the low pressure region and the impossibility of PDA measurements in sprays with non-spherical particles are negligible compared to the final success with PDA during IGA. An on-line control for the gas atomization process has been realized, which is, in principle, also applicable for liquid gas and water atomization, where liquefied gas or water droplets are present simultaneously with molten metal droplets or already solidified metal particles. The required measurement technique, not only for droplet size and velocity, but also for the distinction between metal and atomizing medium has been demonstrated by various experiments. Finally, the application of the on-line PDA and the control loop systems has been successfully transferred from a laboratory system to a pilot plant, which works near to industrial conditions.
Vision-2020, whose objectives include the reduction of emissions and a more effective transport systems, puts severe demands on aircraft velocity and weight. These require an increased load on wings and aero-engine components. The greening of air transport systems means a reduction of drag and losses, which can be obtained by keeping laminar boundary layers on external and internal airplane parts. Increased loads make supersonic flow velocities more prevalent and are inherently connected to the appearance of shock waves, which in turn may interact with a laminar boundary layer. Such an interaction can quickly cause flow separation, which is highly detrimental to aircraft performance, and poses a threat to safety. In order to diminish the shock induced separation, the boundary layer at the point of interaction should be turbulent. The main objective of the TFAST project is to study the effect of transition location on the structure of interaction. The main question is how close the induced transition may be to the shock wave while still maintaining a typical turbulent character of interaction. The main study cases - shock waves on wings/profiles, turbine and compressor blades and supersonic intake flows - will help to answer open questions posed by the aeronautics industry and to tackle more complex applications. In addition to basic flow configurations, transition control methods (stream-wise vortex generators and electro-hydrodynamic actuators) will be investigated for controlling transition location, interaction induced separation and inherent flow unsteadiness. TFAST for the first time will provide a characterization and selection of appropriate flow control methods for transition induction as well as physical models of these devices. Emphasis will be placed on closely coupled experiments and numerical investigations to overcome weaknesses in both approaches.
The main objective of the AEROMUCO project is to develop and evaluate a number of alternative The high-speed airflow over aircraft can contain sand, water droplets, insects, ice crystals and other particles, and there thus exists a significant challenge to produce protective coatings for this varied and demanding environment. AEROMUCO will develop multifunctional coatings with both anti-contamination and anti-icing properties that will also protect the aircraf The multi-disciplinary approach will yield technological improvements beyond the state of the art through a structured, but innovative, research strategy. A comprehensive set of unique tests will be performed, including ice build-up tests (microscopic and full-scale icing wind tunnel tests), comparative rain erosion tests, abrasion tests, and an assessment of kinetic of enzyme processes.
The goal of ERICKA is to directly contribute to reductions in aircraft engine fuel consumption with a targeted contribution of 1Prozent reduction in SFC relative to engines currently in service. The fuel efficiency of a jet engine used for aircraft propulsion is dependent on the performance of many key engine components. One of the most important is the turbine whose efficiency has a large influence on the engine fuel consumption and hence its CO2 emissions. The turbine must operate with high efficiency in the most hostile environment in the engine. The design of turbine cooling systems remains one of the most challenging processes in engine development. Modern high-pressure turbine cooling systems invariably combine internal convection cooling with external film cooling in complex flow systems whose individual features interact in complex ways. The heat transfer and cooling processes active are at the limit of current understanding and engine designers rely heavily on empirical tools and engineering judgement to produce new designs. ERICKA will provide a means of improving turbine blade cooling technology that will reduce turbine blade cooling mass-flow relative to that required using existing technology. A reduction in cooling mass-flow leads directly to improved component and engine efficiency. The improved technology for turbine cooling developed by ERICKA will also enable low NOx combustion chambers to be included in future engines. ERICKA will undertake research to furnish better understanding of the complex flows used to internally cool rotating turbine blades. This will be achieved by: 1) Acquisition of high quality experimental data using static and rotating test facilities 2) Development of cooling design capability by enhancement of computer codes that will exploit these experimental data ERICKA groups 18 partners representing the European aero engine industry, five SMEs and a set of leading academic institutions. Prime Contractor: Rolls-Royce PLC; London; United Kingdom.
Reducing noise from aircraft operations perceived by airport neighbouring communities is a major challenge facing the aircraft manufacturing industry, social society and the air transport business. By adopting a whole aircraft approach based on the latest developments in active / adaptive technologies, flow control techniques and advances in computational aero-acoustics applied to the major causes of noise at source, OPENAIR aims to deliver a step change in noise reduction, beyond the SILENCE(R) achievements. The workplan clearly supports realistic exploitation of promising design concepts driven by noise reduction and will result in the development and validation up to TRL 5 of ?2nd Generation? technology solutions. OPENAIR?s multidisciplinary approach and composition is suited to the projected integrated, lightweight solutions. The process includes a down-selection in mid project. The selected technologies will be subjected to scaled rig tests, and the resulting data will support assessment of the noise reduction solutions on powerplant and airframe configurations across the current and future European range of products. The project exploitation plan will include detailed proposals for further demonstration in the Clean Sky JTI. The verification of the technologies applicability will be assured by addressing identified integration and environmental tradeoffs (performance, weight, emissions). In this way OPENAIR will develop solutions that can play a significant role, in continuity with the previous Generation 1 effort, enabling future products to meet the ACARE noise goals and improving current fleet noise levels through retrofitting. This capability is key to providing the flexibility needed to simultaneously accommodate market requirements in all segments, global traffic growth and environmental constraints, while addressing the global environmental research agenda of the EU. Prime Contractor: Snecma SA; Paris; France.
Due to continuous efforts through past and ongoing European projects, lean combustion by means of internally staged injectors now appears to be the promising technology for obtaining the required emission reductions compatible with a sustainable growth of aviation transport. (cf ACARE 2020). Recognising that putting into service such a technology as soon as possible is the only way to effectively reduce the aviation environmental impact, TECC-AE addresses some unavoidable issues in order to: - Solve the main limitations identified during past and ongoing projects appearing when lean combustion is pushed toward its maximum potential about NOx emissions reduction. In particular, TECC-AE will a) Provide full combustor operability in terms of ignition, altitude relight and weak extinction performance b) Suppress the occurrence of thermo-acoustic instabilities by reducing the combustor sensitivity to unsteady features to a level such instabilities will not happen - Ensure injection system robustness with respect to coking that can appears during transient operations of the engine. - Optimise the combustion system s operational and environmental performance through all the flight phases - Develop, demonstrate and validate design rules, CFD capabilities and scaling laws. Prime Contractor: SNECMA SA; Paris; France.
Objective: This proposal has been prepared in the framework of a research and development roadmap defined by the European rotorcraft community that aims to develop a civil tilt-rotor aircraft. A key target of the road map is a flying demonstrator in the 2010 decade. NICETRIP specifically addresses the acquisition of new knowledge and technology validation concerning tilt-rotor. The main project objectives are: - To validate the European civil tilt-rotor concept based on the ERICA architecture; - To validate critical technologies and systems through the development, integration and testing of components of a tilt-rotor aircraft on full-scale dedicated rigs; - To acquire new knowledge on tilt-rotor through the development and testing of several wind tunnel models, including a large-scale full-span powered model; - To investigate and evaluate the introduction of tilt-rotors in the European Air Traffic Management System; - To assess the sustainability of the tilt-rotor product with respect to social and environmental issue s and to define the path towards a future tilt-rotor flying demonstrator. Project NICETRIP is fully relevant to the strategic objective 1.3.2.1: - Integration of technologies towards the future tilt-rotor aircraft, of the work programme of call 3 of the Thematic Priority Aeronautics and Space. The organisation and resources proposed to achieve the project objectives include a 54-month work plan made of 7 work packages and a consortium of 31 participants, fully representing the span of needed capabilities.
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