Objective The High Pressure Turbine is a particularly sensitive engine component. The blade life duration, the efficiency and the fuel consumption are critical issues. The trends are to increase the turbine inlet temperature for unimproved cycle and the stage load to reduce the engine weight. The new generation of low Knox emission combustion chambers impose aggressive inlet conditions with hot spots and swirl. The film cooling used to protect blades from hot gas must be optimised not to be detrimental to the fuel consumption. The sources of aerodynamic losses need to be quantified and graded in unsteady flows. Not to penalise the performance, the turbine design must combined opposite constraints. So, heat transfer and aerodynamic losses in unsteady turbine external flows must be predicted more precisely. The physical understanding of such complex phenomena is mandatory for improved design practices. Numerous small-scale technological effects and advanced modelling must be considered for design tools to increase their prediction capability. The project aims at building experimental databases needed for design tools validation. Detailed 3D unsteady measurements in engine representative configurations will be performed. The measurement of turbine efficiencys a European first in full scale short duration rigs and will permit to quantify the effects of inlet swirl, enhanced hot spots, rotor platform cooling, high pressure stage with strong shock waves and a new architecture of low-pressure vane which combines structural struts. More fundamental research will be carried out for detailed film cooling efficiency in transonic flows, with whole entrance effect and in multi-row configurations. The industrial partners will validate and assess their design tools against experimental results. The resulting capability for turbine blade and film cooling optimised design will lead to a reduction of coolant mass flow from15% to 12% and a 20% weight loss. Fields of science natural sciencescomputer and information sciencesdatabasesnatural sciencesphysical sciencesclassical mechanicsfluid mechanicsfluid dynamicscomputational fluid dynamicsengineering and technologymechanical engineeringvehicle engineeringaerospace engineeringaeronautical engineeringengineering and technologyenvironmental engineeringenergy and fuelsnatural sciencesmathematicsapplied mathematicsnumerical analysis Programme(s) FP6-AEROSPACE - Aeronautics and Space: thematic priority 4 under the Focusing and Integrating Community Research programme 2002-2006. Topic(s) AERO-2002-1.3.1.1g - Propulsion Call for proposal FP6-2002-AERO-1 See other projects for this call Funding Scheme STREP - Specific Targeted Research Project Coordinator SNECMA EU contribution No data Address 2 Bd du General Martial-Valin PARIS France See on map Total cost No data Participants (6) Sort alphabetically Sort by EU Contribution Expand all Collapse all MTU AERO ENGINES GMBH Germany EU contribution No data Address Dachauer Strasse 665 MUENCHEN See on map Total cost No data TURBOMECA SA France EU contribution No data Address Avenue du President Szydlowski BORDES (BIZANOS) See on map Total cost No data INDUSTRIA DE TURBOPROPULSORES SA Spain EU contribution No data Address Parque Tecnologico, Edificio 300 ZAMUDIO-VIZCAYA See on map Total cost No data THE CHANCELLOR, MASTERS AND SCHOLARS OF THE UNIVERSITY OF OXFORD United Kingdom EU contribution No data Address University Offices, Wellington Square OXFORD See on map Links Website Opens in new window Total cost No data ACIES SARL France EU contribution No data Address Rue de la republique 69 LYON See on map Total cost No data ROLLS-ROYCE DEUTSCHLAND LTD & CO. KG Germany EU contribution No data Address Eschenweg 11 Dahlewitz See on map Links Website Opens in new window Total cost No data
