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Toward Innovative Methods for Combustion Prediction in Aero-Engines

Toward Innovative Methods for Combustion Prediction in Aero-Engines

Objective

The aim of the TIMECOP-AE project is to provide the necessary combustion prediction methods that enable the development of practical advanced combustion systems for future engines that will reduce emission levels and fuel consumption. Predictive tools are required to be able to reduce NOx emissions, to decrease the development time and costs of new combustion systems and to improve the operability of lean-burn combustion systems.

All promising approaches to satisfy future emission levels regulations are based on lean combustion technology. However, lean combustion compromises combustor operability, including ignition, altitude re-light, pull-away, weak extinction performance and thermo-acoustic instability behaviour. It is of prime importance to evaluate this transient behaviour in the design stage to ensure good operability. Without these tools the development of these advanced combustion systems will depend on many rig tests.

These are costly and time consuming and will reduce our competitiveness. During the last five years big advances have been made in the field of reactive Large Eddy Simulation (LES) with gaseous fuels. This approach gives promising results with respect to turbulence modelling and can be used to model unsteady processes. Within this proposal the LES tools will gain the capability for modelling the combustion process within conventional and Low Emission combustors over a wide range of operating conditions on liquid fuels.

The operating conditions include mentioned transient phenomena. To be able to model these phenomena improvements are required in the models of turbulence, chemistry, turbulence-chemistry interactions, and liquid spray models. The methods and models will be evaluated against high quality validation data, which will be obtained by several validation experiments. Some are designed to validate specific models, and one is a generic combustor, representative of an aero-engine combustor, and permits to assess the full range of models.

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Coordinator

TURBOMECA S.A.

Address

Avenue Du President Szydlowski
Bordes

France

Administrative Contact

Thomas LEDERLIN (Mr)

Participants (22)

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ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

Germany

ROLLS-ROYCE PLC

United Kingdom

MTU AERO ENGINES GMBH

Germany

SNECMA

France

AVIO SPA

Italy

OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AÉROSPATIALES'

France

DEUTSCHES ZENTRUM FUER LUFT- UND RAUMFAHRT E.V.

Germany

INSTITUT NATIONAL POLYTECHNIQUE DE TOULOUSE

France

CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE

France

CENTRALE RECHERCHE SA

France

FOUNDATION FOR RESEARCH AND TECHNOLOGY

Greece

IFP ENERGIES NOUVELLES

France

THE CHANCELLOR, MASTERS AND SCHOLARS OF THE UNIVERSITY OF CAMBRIDGE

United Kingdom

TECHNISCHE UNIVERSITÄT DARMSTADT

Germany

UNIVERSITY OF KARLSRUHE, INSTITUT FÜR THERMISCHE STRÖMUNGSMASCHINEN

Germany

TECHNISCHE UNIVERSITEIT EINDHOVEN

Netherlands

IMPERIAL COLLEGE OF SCIENCE, TECHNOLOGY AND MEDICINE

United Kingdom

LOUGHBOROUGH UNIVERSITY

United Kingdom

CZESTOCHOWA UNIVERSITY OF TECHNOLOGY

Poland

DEPARTMENT OF MECHANICS AND AERONAUTICS, UNIVERSITY OF ROME "LA SAPIENZA"

Italy

CENTRE EUROPEEN POUR LA RECHERCHE ET LA FORMATION AVANCEE EN CALCULS SCIENTIFIQUES

France

CENTRO DE INVESTIGACIONES ENERGETICAS, MEDIOAMBIENTALES Y TECNOLOGICAS

Spain

Project information

Grant agreement ID: 30828

  • Start date

    1 June 2006

  • End date

    30 November 2010

Funded under:

FP6-AEROSPACE

  • Overall budget:

    € 7 110 272

  • EU contribution

    € 4 800 000

Coordinated by:

TURBOMECA S.A.

France