ITURB

Optimal High-Lift Turbine Blade Aero-Mechanical Design

 Coordinatore UNIVERSITA DEGLI STUDI DI GENOVA 

 Organization address address: VIA BALBI 5
city: GENOVA
postcode: 16126

contact info
Titolo: Prof.
Nome: Pietro
Cognome: Zunino
Email: send email
Telefono: +39 320 4320006
Fax: +39 010 3532566

 Nazionalità Coordinatore Italy [IT]
 Totale costo 839˙100 €
 EC contributo 629˙325 €
 Programma FP7-JTI
Specific Programme "Cooperation": Joint Technology Initiatives
 Code Call SP1-JTI-CS-2012-01
 Funding Scheme JTI-CS
 Anno di inizio 2012
 Periodo (anno-mese-giorno) 2012-10-01   -   2015-06-30

 Partecipanti

# participant  country  role  EC contrib. [€] 
1    UNIVERSITA DEGLI STUDI DI GENOVA

 Organization address address: VIA BALBI 5
city: GENOVA
postcode: 16126

contact info
Titolo: Prof.
Nome: Pietro
Cognome: Zunino
Email: send email
Telefono: +39 320 4320006
Fax: +39 010 3532566

IT (GENOVA) coordinator 306˙420.00
2    UNIVERSITA DEGLI STUDI DI FIRENZE

 Organization address address: Piazza San Marco 4
city: Florence
postcode: 50121

contact info
Titolo: Prof.
Nome: Toni
Cognome: Paolo
Email: send email
Telefono: 390555000000
Fax: 390555000000

IT (Florence) participant 262˙500.00
3    UNIVERSITA DEGLI STUDI DI PADOVA

 Organization address address: VIA 8 FEBBRAIO 2
city: PADOVA
postcode: 35122

contact info
Titolo: Prof.
Nome: Ernesto
Cognome: Benini
Email: send email
Telefono: +39 049 8276767
Fax: +39 049 8276785

IT (PADOVA) participant 60˙405.00

Mappa


 Word cloud

Esplora la "nuvola delle parole (Word Cloud) per avere un'idea di massima del progetto.

maintenance    hub    investigations    flow    optimized    lpt    tests    optimisation    geometries    weight    baseline    laboratory    neural    tools    turbine    numerical    consumption    pressure    innovative    reduce    aerodynamic    blade    iturb    cold    techniques    networks    modern    performed    optimization    emissions    representative    stresses    radial    geometrical    experimental    artificial    fuel    engine    lift    configurations    performance    constraints    configuration    rotor    blades    mechanical   

 Obiettivo del progetto (Objective)

'The need for high speed low pressure turbine modules to be used with innovative aircraft engine concept establishes critical mechanical constraints with very high hub stresses for the rotor blades, thus representing a real challenge for the design. In order to assist the designer with reliable tools it is mandatory to assess the performance of turbine rotor blades of innovative concept with both numerical and experimental investigations. Starting from a baseline configuration, representative of the state-of-the-art of LPT high-lift rotor blades, an aerodynamic optimization will be performed exploiting modern optimization techniques. These techniques are based on the coupling between fast and flexible parametric handling of the geometries, CFD computations and meta-models like Artificial Neural Networks (ANN) or Radial Basis Functions (RBF). Such an approach will accomplish a multi-objective design aimed at enhancing the aerodynamic performance while meeting mechanical and geometrical constraints. Tests will be performed on both baseline and optimized rotors within a cold-flow, large-scale laboratory turbine. Tests on turbine configuration will ensure the reproduction of the correct radial equilibrium effects as well as of the rotor-stator aerodynamic interaction. The Reynolds number will be investigated in the range between 50000 and 300000, which represents the operative range of the LP rotor blades of the engine. The large scale of the facility will allow detailed aerodynamic investigations, and an accurate performance analysis. The numerical and experimental frameworks will allow one to validate and verify the optimized solution and to highlight the key features of the new design with respect to the baseline. The validation of the design and optimization procedures will be accomplished with the availability of detailed experimental data obtained for the innovative rotor blade row in a realistic environment.'

Introduzione (Teaser)

Increasing aerodynamic lift in a turbine rotor blade design that simultaneously decreases weight and maintenance costs could have major benefits when it comes to performance, fuel consumption and emissions. Scientists are optimising the design.

Descrizione progetto (Article)

High-lift low-pressure turbine (LPT) blades enable a reduction in the number of turbine blades in modern gas turbine engines, which can reduce maintenance costs along with weight and associated emissions. However, maintaining stability, performance and safety with fewer blades and very high hub stresses requires careful optimisation of parameters.

In order to meet the challenging design constraints imposed by the unique aerodynamic profile of high-lift LPT rotor blades, an Italian consortium launched the EU-funded project 'Optimal high-lift turbine blade aero-mechanical design' (ITURB). The team is exploiting advanced optimisation techniques based on geometries, computational fluid dynamics and other paradigms such as artificial neural networks.

The combined strengths of the optimisation procedures will lead to aerodynamically sound configurations within mechanical and geometrical constraints. The baseline and optimised rotor configurations will be tested in a cold-flow large-scale laboratory turbine.

During the first 18 months, the advanced aerodynamic optimisation techniques were applied to representative state-of-the-art high-lift LPT rotor blades. In parallel, the laboratory turbine was installed and updated to enhance measurement accuracy and make it possible to investigate additional parameters. In particular, the external radius was enlarged and the hub modified to accommodate larger blade aspect ratios (span versus mean chord of the aerofoil). Several modifications were designed to change flow or facilitate its measurement and to enable measurement of blade loading on the rotor.

The high-lift LPT rotor blade configuration promises lower weight, fuel consumption and emissions, and forms an important part of the Clean Sky initiative to reduce the environmental impact of air travel. The ITURB theoretical and experimental design and testing tools will enable optimisation of the blades and comparison to baseline performance in support of that effort.

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