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DEVELOPMENT OF ADVANCED ACTUATION CONCEPTS TO PROVIDE A STEP CHANGE IN TECHNOLOGY USED IN FUTURE AERO-ENGINE CONTROL SYSTEMS (ADVACT)

DEVELOPMENT OF ADVANCED ACTUATION CONCEPTS TO PROVIDE A STEP CHANGE IN TECHNOLOGY USED IN FUTURE AERO-ENGINE CONTROL SYSTEMS (ADVACT)

Objective

Major strides have been made in monitoring and control for gas turbines engines. Very little has changed in what is physically controlled or the actuator mechanisms themselves. Variables on civil aircraft remain largely restricted to fuel input, guide vanes and bleed valves. All other components redesigned as a compromise between efficiency at different operating conditions and the need to maintains table operation over the entire operating range. Recent developments in available actuation mechanisms have been identified as providing many opportunities for new control functions that could provide a major step change in the capabilities of the machines. Internal company reviews and internationally reported programmes have identified many control functions and mechanisms that could be used. Just one application of these technologies has already been identified as saving 0.3M Euro per aircraft year on transatlantic flights and a fleet CO2reduction of 8M Tonnes per year by 2020There is a continual push to improve system performance for a number of commercial and legislative objectives. These can be largely grouped as cost, competitive position and environmental impact. Advanced Actuation will help to address these issues with improved engine performance. To achieve this there is a need for imaginative research into the basic technologies that have already been identified and extensive studies to consider the manufacturing, operational and environmental issues.

The programme has three main elements;

Quantify the performance and operational benefits of extended actuation capabilities.

Research into selected technologies for the gas turbine environment (MEMS, SMA, Advanced Electromagnetics, Boundary Layer Manipulation and Active Vibration Control).

Evaluate the selected technologies in key applications (egg. variable nozzle, "virtual" VGV, tip seals)

Coordinator

ROLLS ROYCE PLC

Address

Buckingham Gate 65
London

United Kingdom

Administrative Contact

Buffone COSIMO (Mr)

Participants (17)

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MTU AERO ENGINES GMBH

Germany

SNECMA SA

France

AVIO S.P.A.

Italy

AVIO S.P.A.

Italy

UNIVERSITY OF SHEFFIELD

United Kingdom

TURBOMECA SA

France

UNIVERSITY OF BIRMINGHAM

United Kingdom

TECHNISCHE UNIVERSITAET DRESDEN

Germany

INSTITUT NATIONAL DES SCIENCES APPLIQUEES DE TOULOUSE

France

THE CHANCELLOR, MASTERS AND SCHOLARS OF THE UNIVERSITY OF CAMBRIDGE

United Kingdom

CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE

France

INDUSTRIA

France

OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES

France

POLITECNICO DI TORINO

Italy

CRANFIELD UNIVERSITY

United Kingdom

VON KARMAN INSTITUTE FOR FLUID DYNAMICS

Belgium

DAIMLER CHRYSLER AG

Germany

Project information

Grant agreement ID: 502844

  • Start date

    1 July 2004

  • End date

    31 December 2008

Funded under:

FP6-AEROSPACE

  • Overall budget:

    € 6 634 100

  • EU contribution

    € 4 394 886

Coordinated by:

ROLLS ROYCE PLC

United Kingdom