Cel 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. Dziedzina nauki 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 Program(-y) FP6-AEROSPACE - Aeronautics and Space: thematic priority 4 under the Focusing and Integrating Community Research programme 2002-2006. Temat(-y) AERO-2002-1.3.1.1g - Propulsion Zaproszenie do składania wniosków FP6-2002-AERO-1 Zobacz inne projekty w ramach tego zaproszenia System finansowania STREP - Specific Targeted Research Project Koordynator SNECMA Wkład UE Brak danych Adres 2 Bd du General Martial-Valin PARIS Francja Zobacz na mapie Koszt całkowity Brak danych Uczestnicy (6) Sortuj alfabetycznie Sortuj według wkładu UE Rozwiń wszystko Zwiń wszystko MTU AERO ENGINES GMBH Niemcy Wkład UE Brak danych Adres Dachauer Strasse 665 MUENCHEN Zobacz na mapie Koszt całkowity Brak danych TURBOMECA SA Francja Wkład UE Brak danych Adres Avenue du President Szydlowski BORDES (BIZANOS) Zobacz na mapie Koszt całkowity Brak danych INDUSTRIA DE TURBOPROPULSORES SA Hiszpania Wkład UE Brak danych Adres Parque Tecnologico, Edificio 300 ZAMUDIO-VIZCAYA Zobacz na mapie Koszt całkowity Brak danych THE CHANCELLOR, MASTERS AND SCHOLARS OF THE UNIVERSITY OF OXFORD Zjednoczone Królestwo Wkład UE Brak danych Adres University Offices, Wellington Square OXFORD Zobacz na mapie Linki Strona internetowa Opens in new window Koszt całkowity Brak danych ACIES SARL Francja Wkład UE Brak danych Adres Rue de la republique 69 LYON Zobacz na mapie Koszt całkowity Brak danych ROLLS-ROYCE DEUTSCHLAND LTD & CO. KG Niemcy Wkład UE Brak danych Adres Eschenweg 11 Dahlewitz Zobacz na mapie Linki Strona internetowa Opens in new window Koszt całkowity Brak danych
