Description du projet
Mesurer en temps réel la distorsion de l’air à l’entrée des moteurs aéronautiques
Les conceptions complexes d’admission d’air pour les turboréacteurs à très haut taux de dilution provoquent une distorsion notable au niveau de la face du réacteur au moment du décollage. Cela peut nuire aux performances du moteur, à l’intégrité structurale et à la marge de sécurité, avec des conséquences potentiellement catastrophiques pour l’ensemble du système de propulsion. Les techniques actuelles d’essai et de certification des moteurs aéronautiques sont limitées par leur faible résolution spatiale et leur nature intrusive. Le projet NIFTI, financé par l’UE, entend surmonter ces difficultés en mettant au point une technique non intrusive qui fournira des données en temps réel avec une résolution spatiale supérieure d’au moins un ordre de grandeur aux méthodes actuelles. Les résultats théoriques et expérimentaux devraient permettre de mieux comprendre l’aérodynamique complexe des systèmes d’admission à couplage étroit et faciliter la conception future de moteurs aéronautiques tolérants au décrochage.
Objectif
Short and slim aero-engine intake designs for very high bypass ratio configurations cause notable levels of unsteady distortions at the fan face especially under cross-wind or angle of attack operation during aircraft take-off. Such distortions can adversely affect the engine’s performance, operability, structural integrity and safety margin with potentially catastrophic consequences for the entire propulsion system.
Current practices for aero-engine testing and certification rely on a low number of intrusive pressure measurements at the fan face to characterise the distortion levels. Given the known limitations of currently used methods (low spatial resolution, intrusive nature) the existing technologies are inadequate to reduce the risk on the development and certification of future novel systems.
NIFTI aims to address this gap by demonstrating a non-intrusive technique to measure velocity fields across a plane located upstream of a large diameter fan of a high bypass ratio aero-engine which has never been achieved. This method will provide synchronous datasets across the measurement plane with at least one order of magnitude higher spatial resolution than current methods. The implementation will demonstrate a highly automated and flexible multi-camera system within a representative industrial test environment. A number of more advanced, non-intrusive measuring technologies will be assessed such as 3D PTV or Helium Filled Soap Bubbles (HFSB) to further enhance the outputs of the selected baseline solution.
The experimental activities will be supported by numerical campaigns and advanced data processing and flow analysis methods that will be used to analyse the highly unsteady nature of the flow distortions that will be measured during NIFTI’s experimental campaigns. These outcomes will ultimately unlock the complex aerodynamics of closely coupled fan-intake systems and aid the development of novel design rules for future, stall-tolerant aero-engines.
Champ scientifique
- natural scienceschemical sciencesinorganic chemistrynoble gases
- engineering and technologymechanical engineeringvehicle engineeringaerospace engineeringaircraft
- engineering and technologymechanical engineeringvehicle engineeringaerospace engineeringaeronautical engineering
- natural sciencescomputer and information sciencesdata sciencedata processing
Mots‑clés
Programme(s)
Régime de financement
RIA - Research and Innovation actionCoordinateur
8316 PR Marknesse
Pays-Bas