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Turbulence and Transition Modelling for Special Turbomachinery Applications

Turbulence and Transition Modelling for Special Turbomachinery Applications

Objective

The TATMo project addresses the top level objectives outlined in the aeronautics research work programme, namely, improving the environmental impact with regards to emissions by improving the SFC and thus contributing to the reduction of CO2 emissions by 50% in the long term. At the same time, the aircraft operating costs are reduced through a considerable reduction in fuel consumption thus strengthening the competitiveness of European aero-engine industry.

All major European aero-engine manufacturers together with four research institutes and five universities (including one SME) have bundled their expertise and resources into the TATMo project. The outcome of the project will contribute to these objectives through a 1-2% reduction in engine weight due to reduced blade count, 2% reduction in fuel burn due to high efficient blade designs, 5% reduction in aero-engine development costs and 10% reduction in aero-engine time-to-market through improved design tools.

The efficiency of high lift blades for Low Pressure Turbines (LPT) is significantly improved by reducing the undesirable huge separations present at low Reynolds numbers at mid-span using appropriate perturbation devices, e.g. passive roughness elements extending along the spanwise direction of the blade or active measures like synthetic jets. The performance of compressor blades will be improved by avoiding the detrimental corner separations by means of suction and blowing. The effects of real geometry roughness such as fillet radius and weld are assessed as well.

The main objective of TATMo is the improvement of calculation capabilities by a better modelling of the flow with and without spanwise roughness elements and synthetic jets, which is necessary for the prediction of these complicated flow fields and the losses. This will be verified by comparisons between numerical calculations and extensive detailed experiments for compressor as well as for turbine blades.

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Coordinator

MTU AERO ENGINES

Address

Dachauer Strasse 665
Muenchen

Germany

Administrative Contact

Stephan SERVATY (Mr)

Participants (16)

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SNECMA

France

AVIO S.P.A.

Italy

INDUSTRIA DE TURBOPROPULSORES, S.A

Spain

TECHSPACE AERO S.A.

Belgium

ROLLS-ROYCE DEUTSCHLAND LTD & CO. KG

Germany

DEUTSCHES ZENTRUM FÜR LUFT- UND RAUMFAHRT E. V.

Germany

OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AÉROSPATIALES'

France

UNIVERSITA' DEGLI STUDI DI FIRENZE - DIPARTIMENTO DI ENERGETICA "SERGIO STECCO"'

Italy

CENTRE DE RECHERCHE EN AÉRONAUTIQUE, ASBL

Belgium

TECHNISCHE UNIVERSITÄT BERLIN

Germany

THE CHANCELLOR, MASTERS AND SCHOLARS OF THE UNIVERSITY OF CAMBRIDGE

United Kingdom

VON KARMAN INSTITUTE

Belgium

UNIVERSITÀ DEGLI STUDI DI GENOVA - DIPARTIMENTO DI MACCHINE, SISTEMI ENERGETICI E TRASPORTI

Italy

UNIVERSIDAD POLITECNICA DE MADRID

Spain

IMPERIAL COLLEGE OF SCIENCE, TECHNOLOGY AND MEDICINE

United Kingdom

AVIO INVESTMENTS S.P.A.

Italy

Project information

Grant agreement ID: 30939

  • Start date

    1 October 2006

  • End date

    31 March 2010

Funded under:

FP6-AEROSPACE

  • Overall budget:

    € 4 905 970

  • EU contribution

    € 2 999 908

Coordinated by:

MTU AERO ENGINES

Germany