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Main Annulus Gas Path Interactions

Main Annulus Gas Path Interactions

Objective

In a modern aero engine, up to 20% of the main annulus flow is bled off to perform cooling and sealing functions. The vicinity of these bleed ports and flow sinks is characterised by complex unsteady swirling flows, which are not fully understood. Even the most up-to-date numerical tools have difficulties predicting the behaviour of the secondary flow system when interacting with the main annulus. The project addresses interactions between main gas path and secondary flow systems in commercial gas turbines in response to Research Activity AERO-2005-1.3.1.2a Concepts and technologies for improving engine thermal efficiency and reducing secondary air losses. Experiments are planned on turbine disc rim and compressor manifold cavity heat transfer, hot gas ingestion, and spoiling effects of cooling air flow and their impact on turbine and compressor performance, as well as a reduction of secondary air losses.

The experimental data will be used for better understanding of the complex flow phenomena and improvements of platform and cavity design. Furthermore, the industrial partners will validate their design tools with these test data and improve their prediction capability of secondary flow systems when interacting with the main gas path. The expected results are a reduction of cooling and sealing airflow rates, improvements of the turbine and compressor efficiency and increase of the safety margin of the engine components by better cooling.

Expected technical results are:
- Knowledge of the interaction phenomena and its effect on cavity heat transfer, spoiling and performance,
- Experimental results for validation of improved numerical tools for secondary flow systems,
- Optimised design methods and CFD best practice guidelines.

The targeted outcome will contribute to the ACARE goal of reduced CO2 emissions via reduced fuel burn of 2% to improve the environment and strengthening the competitiveness of European gas turbine manufacturers.

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Coordinator

ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

Address

Eschenweg 11
1536 Blankenfelde-Mahlow

Germany

Administrative Contact

Michael KLINGSPORN (Dr)

Participants (15)

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SNECMA

France

ROLLS-ROYCE PLC

United Kingdom

AVIO S.P.A.

Italy

AVIO S.P.A.

Italy

SIEMENS INDUSTRIAL TURBOMACHINERY LTD

United Kingdom

ALSTOM (SWITZERLAND) LTD.

Switzerland

INDUSTRIA DE TURBO PROPULSORES S.A.

Spain

MTU AERO ENGINES GMBH

Germany

TURBOMECA

France

THE UNIVERSITY OF SURREY

United Kingdom

UNIVERSITY OF SUSSEX

United Kingdom

DARMSTADT UNIVERSITY OF TECHNOLOGY

Germany

UNIVERSITA DEGLI STUDI DI FIRENZE

Italy

UNIVERSIDAD POLITECNICA DE MADRID

Spain

KARLSRUHER INSTITUT FÜR TECHNOLOGIE

Germany

Project information

Grant agreement ID: 30874

  • Start date

    1 September 2006

  • End date

    31 August 2011

Funded under:

FP6-AEROSPACE

  • Overall budget:

    € 6 186 996

  • EU contribution

    € 4 300 000

Coordinated by:

ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

Germany