Aerothermal Investigations on Turbine End-walls and Blades II

Today's market for civil aircraft continuously demands lighter, cheaper, more efficient, cleaner and quieter engines. For the turbine component of a competitive future aero-engine, these requirements result in higher thermal loads in the high-pressure stage due to flatter temperature traverses at the turbine inlet as a result of new combustion concepts, and hence, the need for advanced cooling concepts. Moreover, the weight and cost requirements lead to high or ultra-high lift blade concepts for the decreasing number of parts, and to unshrouded blade concepts to decrease weight while maintaining a high efficiency level. Finally, the demand for higher by-pass ratios leads to more advanced designs of interducts (so-called aggressive) in order to shorten the axial component length. Consistent with the ACARE goals, the resulting impact on turbine design and aircraft systems is referenced to the baseline of proven in-flight technology for a two-stage high-pressure turbine as of 2000. The following objectives are stated for the turbine design: 20% reduction in turbine weight, 10% reduction in coolant consumption, 1.5% increase in turbine efficiency, 50% reduction in time for detailed design with state-of-the-art CFD tools and 20% decrease in uncertainty of wall temperature prediction, thereby leading to a 20% reduction in time-to-market, a 10% reduction in cost and a 1% reduction in CO2 emissions for an entire aero-engine. The AITEB-2 project will lead to short-term benefits in terms of lighter and more efficient turbine modules, whereas the mid-term and long-term benefits of the project will be seen in combining the results of the present project with other projects running within the Sixth Framework Programme, such as AIDA and TATEF-2. By covering both aerodynamic and aerothermal aspects of ambitious future turbine designs, the development of highly efficient, low-noise and ultra-high, by-pass ratio, commercial aero engines will be possible.

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  • Supplemental Notes:
    • Research institutions undertaking the sub-projects: MTU Aero Engines GmbH, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), Universität Karlsruhe (Technische Hochschule), Universität der Bundeswehr München, SNECMA, Turbomeca S.A., AVIO S.p.A., Università degli Studi di Firenze, Instytut Maszyn Przeplywowych im. Roberta Swewalskiego Polskiej Akademii Nauk, Aero Corporation AB, Chalmers Tekniska Högskola AB, ALSTOM Power (UK) Ltd., Siemens Industrial Turbomachinery Ltd. (SIT), Cambridge Flow Solution, Ltd., and the University of Cambridge.


  • English


  • Status: Active
  • Sponsor Organizations:

    Strengthening Competitiveness

    6th RTD Framework Programme
    European Union
    Brussels,   Belgium 
  • Project Managers:

    Janke, Erik

  • Start Date: 20060301
  • Actual Completion Date: 20090331
  • Source Data: RiP Project 25429

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Filing Info

  • Accession Number: 01461629
  • Record Type: Research project
  • Source Agency: Transport Research Knowledge Centre
  • Files: RiP
  • Created Date: Jan 3 2013 1:49PM