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Turbine Aero-Thermal External Flows 2 (TATEF2)

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.

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Coordinator

SNECMA

Address

2 Bd Du General Martial-Valin
Paris

France

Administrative Contact

Rémi OLIVE (Mr)

Participants (6)

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MTU AERO ENGINES GMBH

Germany

TURBOMECA SA

France

INDUSTRIA DE TURBOPROPULSORES SA

Spain

THE CHANCELLOR, MASTERS AND SCHOLARS OF THE UNIVERSITY OF OXFORD

United Kingdom

ACIES SARL

France

ROLLS-ROYCE DEUTSCHLAND LTD & CO. KG

Germany

Project information

Grant agreement ID: 502924

  • Start date

    1 July 2004

  • End date

    31 December 2008

Funded under:

FP6-AEROSPACE

  • Overall budget:

    € 8 245 755

  • EU contribution

    € 5 232 040

Coordinated by:

SNECMA

France