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Turbine Aero-Thermal External Flows 2 (TATEF2)

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 efficiency’s 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.

Call for proposal

FP6-2002-AERO-1
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Funding Scheme

STREP - Specific Targeted Research Project

Coordinator

SNECMA
Address
2 Bd Du General Martial-valin
Paris
France

Participants (6)

MTU AERO ENGINES GMBH
Germany
Address
Dachauer Strasse 665
Muenchen
TURBOMECA SA
France
Address
Avenue Du President Szydlowski
Bordes (Bizanos)
INDUSTRIA DE TURBOPROPULSORES SA
Spain
Address
Parque Tecnologico, Edificio 300
Zamudio-vizcaya
THE CHANCELLOR, MASTERS AND SCHOLARS OF THE UNIVERSITY OF OXFORD
United Kingdom
Address
University Offices, Wellington Square
Oxford
ACIES SARL
France
Address
Rue De La Republique 69
Lyon
ROLLS-ROYCE DEUTSCHLAND LTD & CO. KG
Germany
Address
Eschenweg 11
Dahlewitz