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Internal Cooling of Turbine Blades

Objective



Objectives and content
This proposal is aimed at the 3A.3. 'Technologies for
Improved Aircraft Efficiency' section of the IMT work
program. The use of state-of-the art technology for
aircraft design is paramount to keep European
manufacturers competitive in world markets and benefits
not only the aircraft manufacturer but also the European
Community. The overall financial impact of this proposal
for the partners is estimated at 25 BECU over the next
five years, which could be lost, if the European
suppliers lose competitiveness.
More specifically, this proposal is directed at the
propulsion technologies 3A.3.9. Task to develop and
validate numerical methods for design and off-design
analysis of turbomachinery components and in particular
the internal cooling of turbine blades. The estimated
economic impact from this project alone is some 200 MECU
over the next five years for the industrial partners.
Internal cooling of modern turbine blades is essential
for efficient engine performance and predictable blade
lives. Blade cooling benefits specific thrust and
efficiency by allowing higher cycle temperatures to be
employed, however, bleed air used for cooling, imposes
cycle penalties and reduces aerodynamic efficiencies.
Cooling research aims to develop and validate improved
design methodologies that give maximum cooling
effectiveness for minimum cooling flow. The design
methods need to be reliable reducing risk in future
projects helping to avoid in-service short falls and high
maintenance costs.
Design methods have been almost exclusively derived from
experiments performed using simplified cooling geometries
and without the influence of rotation, which is perfectly
feasible for nozzle guide vane designs but sadly lacking
for rotor designs. However, it is important to pursue
both static and rotating experiments to establish the
effects of rotation and to establish design rules that
would allow corrections to static experimental data.
All experimental data can then be used to validate CFD
modelling which currently has difficulty in predicting
heat transfer levels in highly turbulent internal cooling
flows.

Funding Scheme

CSC - Cost-sharing contracts

Coordinator

Rolls Royce PLC
Address

BS12 7QE Filton - Bristol
United Kingdom

Participants (10)

ABB Kraftwerke Ltd
Switzerland
Address

5401 Baden
ALSTOM POWER UK LTD.
United Kingdom
Address
Lindum House, 11 Sewell Road
Lincoln
BMW Rolls-Royce GmbH - Aeroengines
Germany
Address
11,Eschenweg
15827 Dahlewitz
Fiat Avio SpA
Italy
Address
312,Via Nizza
10127 Torino
MTU AERO ENGINES GMBH
Germany
Address
Dachauer Strasse 665
80995 München
Rolls Royce PLC
United Kingdom
Address

BS12 7QE Bristol
SWISS FEDERAL INSTITUTE OF TECHNOLOGY LAUSANNE
Switzerland
Address
Ecublens
1015 Lausanne
Société Nationale d'Etudes et de Construction de Moteurs d'Aviation
France
Address

77550 Moissy-cramayel
University of Wales, Swansea
United Kingdom
Address
Singleton Park
SA2 8PP Swansea
Universität Darmstadt/TU
Germany
Address
30,Petersenstraße
64287 Darmstadt