Goals and Strategies for Open Fan Design

Carola Rovira Sala^1,2, Thomas Dygutsch¹, Christian Frey¹, Rainer Schnell¹, Raul Martinez Luque³

1: German Aerospace Center (DLR), Germany; 2: Universidad Politécnica de Madrid, Spain; 3: Safran Aircraft Engines, France

Experimental Studies of Shock Wave Boundary Layer Interaction on suction side of fan representative profile

Ahmed H. Hanfy, Pawel Flaszyński, Piotr Doerffer, Piotr Kaczyński

Institute of Fluid-Flow Machinery, Polish Academy of Sciences (IMP PAN), Poland

Aerodynamics of a Short Intake at High Incidence

Fernando Tejero¹, David MacManus¹, Josep Hueso Rebassa¹, Yuri Frey Marioni², Ian Bousfield²

1: Cranfield University; 2: Rolls-Royce plc

Body Force Modelling of a Multi-Stage High-Pressure Compressor under Inlet Distortion

Chiara Crea¹, Julien Marty², Raphaël Barrier², Sébastien Cochon¹, Guillaume Dufour³

1: Safran Aircraft Engines, 77550 Moissy Cramayel, France; 2: DAAA, ONERA, Institut Polytechnique de Paris, 92190 Meudon, France; 3: ISAE-SUPAERO, Université de Toulouse, 31055 Toulouse, France

Estimation of intra-scale transfer rates within a compressor flowfield using high-fidelity data

Pawel Jan Przytarski, Matteo Dellacasagrande, Davide Lengani

University of Genova, Italy

Application of a novel pseudo-spectral time-marching method to turbomachinery

Jesus Matesanz-Garcia, Roque Corral

Universidad Politécnica de Madrid, Spain

Variation of tip clearance and incidence to induce rotating instabilities in a linear compressor cascade

Christoph Jasmund, Martin Lange, Ronald Mailach

Technische Universität Dresden, Germany

Experimental investigation by Particle Image Velocimetry of the active flow control of the stall inception of an axial compressor

Olha Alekseik², Pierric Joseph¹, Olivier Roussette¹, Antoine Dazin¹

1: Arts et Métiers; 2: AMVALOR

The Effect of a Variable Cantilevered Stator on 1.5-stage Transonic Compressor Performance

Benedikt Radermacher¹, Fabian Klausmann¹, Felix Jung¹, Jonas Bargon¹, Heinz-Peter Schiffer¹, Bernd Becker², Patrick Grothe²

1: TU Darmstadt, Germany; 2: Rolls-Royce Deutschland

How inlet flow inhomogeneities can affect the transition to stall in an axial compressor?

Francesco Romanò¹, Clemence Rannou^1,2, Alberto Baretter¹, Julien Marty², Pierric Joseph¹, Antoine Dazin¹

1: Univ. Lille, CNRS, ONERA, Arts et Métiers Institute of Technology, Centrale Lille, UMR 9014-LMFL-Laboratoire de Mécanique des Fluides de Lille - Kampé de Fériet, Av. Paul Langevin, Villeneuve-d’Ascq, Lille, F-59000, Hauts de France, France; 2: Département Aérodynamique, Aéroélasticité, Acoustique, Office National d’Études et de Recherches Aérospatiales (ONERA), Université Paris Saclay, F-92190 Meudon, France

A comparative study of varying incidence angle effects on a low-Reynolds-number compressor cascade based on experiments, low-fidelity and high-fidelity numerical simulations

Michael Bergmann, Christian Morsbach, Felix M. Möller, Alexander Hergt, Georgios Goinis, Björn Klose

German Aerospace Center (DLR), Germany

Liquid droplet breakup mechanisms during the aero-engine washing process

Alessio Suman¹, Andrea Cordone¹, Nicola Zanini¹, Mattia Piovan¹, Michele Pinelli¹, Max Koster², Stefan Kuntzagk², Henrik Weiler², Christian Werner-Spatz²

1: University of Ferrara, Italy; 2: Lufthansa Technik AG, Hamburg

High Fidelity Turbomachinery CFD Simulations Using General-Purpose GPU

Qingyuan Zhuang

Siemens, Netherlands

Introduction and presentation of the test case

Xavier Ottavy², Christoph Brandstetter¹

1: Ecole Centrale de Lyon, CNRS, Universite Claude Bernard Lyon 1, INSA Lyon, LMFA, UMR5509, F-69134 Ecully, France; 2: CNRS, Ecole Centrale de Lyon, INSA Lyon, Universite Claude Bernard Lyon 1, LMFA, UMR5509, F-69134 Ecully, France

ECL5/CATANA: Comparative Analysis of Advanced Blade Vibration Measurement Techniques

Christoph Brandstetter¹, Alexandra Schneider¹, Anne-Lise Fiquet¹, Benoit Paoletti², Kévin Billon³, Xavier Ottavy²

1: Ecole Centrale de Lyon, CNRS, Universite Claude Bernard Lyon 1, INSA Lyon, LMFA, UMR5509, F-69134 Ecully, France; 2: CNRS, Ecole Centrale de Lyon, INSA Lyon, Universite Claude Bernard Lyon 1, LMFA, UMR5509, F-69134 Ecully, France; 3: Univ. Lyon, Ecole Centrale de Lyon, LTDS UMR 5513, F-69134 Ecully, France

ECL5/CATANA: Transition from Non-Synchronous Vibration to Rotating Stall at transonic speed

Alexandra Patrizia Schneider, Anne-Lise Fiquet, Nathalie Grosjean, Benoit Paoletti, Xavier Ottavy, Christoph Brandstetter

Ecole Centrale de Lyon, CNRS, Universite Claude Bernard Lyon 1, INSA Lyon, LMFA, UMR5509, 69130, Ecully, France

Some experiences about the RANS modeling of UHBR fan: the case of ECL5/CATANA

Lorenzo Pinelli, Maria Malcaus, Giovanni Giannini, Michele Marconcini

Department of Industrial Engineering, University of Florence, Italy

ECL5/CATANA: Stability prediction at design and part speed

Ewan Gunn

Turbostream

Prediction of the Operation Point Influence on ECL5/Catana Fan Blade Geometry

Marc Kainz

ANSYS

Identification of Tip-Leakage Vortex Wandering in Large-Eddy Simulation of ECL5/CATANA Transonic Fan Stage

Allan Beurville¹, Valentin Caries^1,2, Jérôme Boudet¹, Vincent Clair¹, Alexis Giauque¹

1: École Centrale de Lyon, CNRS, Universite Claude Bernard Lyon 1, INSA Lyon, LMFA, UMR5509, 69130, Ecully, France; 2: Safran Aircraft Engines, Moissy-Cramayel, France

Flutter Analysis of the ECL5 Open Fan Testcase Using Harmonic Balance

Christian Frey¹, Stéphane Aubert², Pascal Ferrand², Anne-Lise Fiquet²

1: German Aerospace Center (DLR), Germany; 2: Ecole Centrale de Lyon, France

Open discussion and conclusion

Xavier Ottavy¹, Christoph Brandstetter²

1: Ecole Centrale de Lyon, CNRS, Universite Claude Bernard Lyon 1, INSA Lyon, LMFA, UMR5509, F-69134 Ecully, France; 2: CNRS, Ecole Centrale de Lyon, INSA Lyon, Universite Claude Bernard Lyon 1, LMFA, UMR5509, F-69134 Ecully, France

Design of a small-scale, high rotational speed centrifugal compressor operating with R-290

Renan Emre Karaefe, Sönke Teichel, Ahmet Çokşen

ebm-papst Mulfingen GmbH & Co. KG, Germany

Compressor Surge and Positive-Slope Performance Modelling

Ola Ilseth Pronk, Alberto Serena, Lars Eirik Bakken

Norwegian University of Science and Technology (NTNU)

The INFRa-Rig: A Novel Experimental Setup for Investigating Closely Coupled Propulsors under Varying Operational Conditions

Patrick Brunow¹, Jonas Grubert¹, Jan Gößling³, Maximilian Mennicken², Rainer Schnell², Nick Gottschalk¹, Christoph Bode¹, Jens Friedrichs¹

1: TU Braunschweig, Germany; 2: German Aerospace Center (DLR), Germany; 3: Leibniz University Hannover, Germany

Evaluation of a Body Force Model for an aerodynamic evaluation of fan intake interactions

Jonas Grubert, Jens Friedrichs, Jan Göing

TU Braunschweig, Germany

Optimising blade profiles to extend the operating range in BLI fan application

Andrea Magrini, Marco Casoni, Ernesto Benini

Università Degli Studi di Padova, Italy

A Comparative Investigation of Tip-Loss and Compressibility Correlations for Blade Element Momentum Theory Propeller Performance Analysis

Manuel Casablanca, Andrea Magrini, Francesco De Vanna, Ernesto Benini

Università Degli Studi di Padova, Italy

Total Pressure Distortion Reconstruction Methods from Velocimetry Data within an Aero-engine Intake at Crosswind

Tommaso Piovesan, Pavlos Zachos, David MacManus

Cranfield University, United Kingdom

Variable Amplitude Leading Edge Tubercle Optimization of Rotor 37

Yannik Schulz, Christoph Kuestner, Joop Moritz Kohl, Dajan Mimic

Institute of Turbomachinery and Fluid Dynamics (TFD), Leibniz University Hanover, Germany

A Quasi-Direct Numerical Simulation of a Compressor Blade with Separation Bubbles and Inflow Turbulence.

Guglielmo Vivarelli¹, Joao Anderson Isler¹, Chris Cantwell¹, Francesco Montomoli¹, Spencer Sherwin¹, Yuri Frey-Marioni², Marcus Meyer³, Iftekhar Naqavi², Raul Vazquez-Diaz²

1: Imperial College London, United Kingdom; 2: Rolls-Royce plc Derby; 3: Rolls-Royce Deutschland

Compressor tandem blade: investigation into actuation strategies

Mathias Brach¹, Andrea Rocca², Koen Alfons Hillewaert^1,2

1: Université de Liège, Belgium; 2: Cenaero

Experimental and numerical characterization of the stable operating range of a highly-loaded axial compressor stage

Riccardo Toracchio^1,2, Koen Hillewaert², Fabrizio Fontaneto¹

1: von Karman Institute, Turbomachinery and Propulsion Dept., Rhode-St-Genèse, Belgium; 2: University of Liège, Aerospace and Mechanical Engineering Dept., Liège, Belgium