Elephant at sunset
H2020 CleanSky2 project / Grant Agreement n° 864719

Project CATANA overview


There is increasing evidence that today’s turbojet technology is limited by instabilities arising from non-linear coupling between aerodynamic, aeroelastic and aeroacoustic phenomena. These multi-physical processes are going to become even more important in future architectures, which utilize Ultra-High-Bypass Ratio and lightweight composite fan designs to reduce greenhouse gas emissions and noise. However, enormous knowledge gaps currently exist concerning these processes and the resulting stability boundaries.
To fill these gaps, and to promote the development of efficient and quiet concepts, a comprehensive research programme is carried out in Project CATANA. The programme will provide an open-test-case fan stage and employ unprecedented instrumentation to perform extensive investigations into the nature of multi-physical instabilities. The carbon-fibre fan stage is currently being developed at Ecole Centrale de Lyon and will be aerodynamically and structurally representative of near future low-speed fans. The project is funded by the European Union's Horizon 2020 Research and Innovation programme CleanSky2 under Grant Agreement n° 864719 with a total budget of 2 449 860 €.

Open-Test-Case Fan ECL5/CATANA
Fan test facility PHARE-2

Multi-physical experiments are planned which allow transient investigations with synchronous measurements of aerodynamic, structure-dynamic and acoustic phenomena.
The research concept combines complementary measurement systems and enables the detection of interactive mechanisms where individual systems are insufficient.
To improve the coherence of the aeroelastic results, a study on structural mistuning and intake geometry will be carried out to understand and quantify the sensitivity of occurring instability mechanisms. The database will be completed by a detailed structural analysis of the stage providing modal characteristics of the rotor blades, including structural damping under rotation.

Objectives and Ambition

Project CATANA aims to promote the development of the next generation of Ultra-High-Bypass-Ratio Turbofan engines by closing the knowledge gaps concerning multi-physical interactions which affect performance and limit the stability range.
The global objective of the proposed project CATANA is: To analyse and interpret highly-coupled fluid-mechanical instability mechanisms from a representative composite fan to enable more accurate prediction methods
The envisaged concept to achieve this goal is to provide an open-test-case composite stage with a detailed structural analysis and to perform exhaustive steady and transient investigations with synchronized multi-physical instrumentation at all critical limits of the operating range.

The specific objectives are:
  1. Provide a composite fan stage which can serve as an interdisciplinary benchmark case for aeroelastic and aeroacoustic interactions.
  2. Establish advanced experimental methodologies based on synchronized instrumentations to investigate multi-physical interaction processes in the highly-coupled system.
  3. Provide an exhaustive experimental database to characterize instability mechanisms physically and phenomenologically depending on operating conditions.
  4. Derive the sensitivity of performance and stability towards structural system symmetry (Intentional Mistuning).
  5. Analyse the influence of the intake geometry on system stability.
Ambition of project CATANA is to provide a substantial scientific basis for the advancement of multi-physical methods, necessary to enable the development of future UHBR composite fan engines. The scientific goal is to clearly understand the chain of course leading to instability in low-speed composite fans, particularly to identify and characterize the respective mechanism and to enable the scientific community to exploit the results through complete access to the test geometry and its structural properties.
Within the planned investigations, scientifically interesting operating points need to be identified and analysed repeatedly with actively controlled steady and transient boundary conditions to achieve statistical significance. By application of the presented multi-physical simultaneous instrumentation, a comprehensive image of the occurring phenomena can then be derived using advanced evaluation methods. It is intended to provide a most-reliable dataset together with a detailed evaluation of uncertainty for each applied methodology.
The specific objectives can be separated into a characterization of periodic or stochastic phenomena at steady operating points and transient investigations of instability mechanisms. The figure presents a schematic of the anticipated program. At three investigation speed lines (subsonic, transonic, overspeed) several operating points from unloaded to loaded conditions are planned to be investigated thoroughly towards aerodynamic, acoustic and structural phenomena and their interactions.
The ambition is to identify and understand the respective flutter or stall-driven (convective transport of separated flow regions leading to Non-Synchronous-Vibration NSV) instability mechanisms since those are the most complicated and safety critical phenomena. It is expected for the stage to encounter non-synchronous effects at highly loaded conditions, which are typically dominated by nonlinear convective phenomena (Subsonic/Transonic Stall Flutter, Points 1 and 2) but can be sustained by acoustic interactions with the intake.
At overspeed or unloaded conditions (Points 3-5) acoustic phenomena are expected to dominate the instability process (Supersonic/Choke flutter). Here, the main scientific interest lies in the accurate characterization of the interaction between the shock and the boundary layer which is still very hard to predict in numerical simulations, particularly if the structure is not rigid.

Open Test Case

The main objective for the research fan-stage is to be representative of modern low-speed fans in terms of overall performance and particularly instability behaviour. The concept of project CATANA is to provide a design developed according to objectives which are driven by efficiency and operability to achieve representative instability characteristics.
Thus, it is intended to investigate a completely new fan stage whose design parameters are relevant for applications in the next decade. From the current point of view the most promising research configuration is a UHBR low-speed fan with high subsonic design speed designated to be installed in midrange jets (like an Airbus A320neo). In cooperation with the industrial partner of ECL Safran Aircraft Engines, a set of design parameters has been derived from an extrapolation of state-of-the-art values.
This concerns:
a) general aerodynamic design parameters (Mach Number, blade loading, solidity, aspect ratio, hub-to-tip ratio, mass flow density, tip clearance etc.), and
b) aerodynamic flow characteristics which influence the instability mechanisms, particularly shock patterns and secondary flow structures.
From a structural point of view, the primary objective is that the assembly assures operational safety in the whole investigation range. To minimize the risk of failure, established procedures of the industrial partner are applied. This concerns the methods of calculating static and dynamic structural deformations, treatments of interfaces (non-linear blade/disk connection etc.), applications of material laws and guidelines for mode separations, manufacturing procedures (carbon layer orientations, core integration, etc.). This approach satisfies the demand for structural representativity with a real engine fan.

Evolution of project ECL5

Several years ago an internal project to develop design methods for a low-speed transonic composite fan stage was started at ECL and has led to a promising research configuration that has been recently discussed in the aeroelastic and aeroacoustic research community at ISUAAAT. Even though it is a purely academic development that can be openly shared, the design has been consequently analysed and validated by the industry partner Safran Aircraft Engines to confirm safe operation. A collaboration with a leading manufacturer who is capable to realize the complex design according to aerospace standards has been established to ensure that the fan stage will be available within an early stage of the envisaged project to allow for comprehensive and profound experimental campaigns.
Final Design of Open Test Case ECL5/Catana
The design is tailored for the 3 MW-class test facility PHARE-2 allowing a scale of approximately 1/5 to 1/3 of an engine fan. According to known similarity parameters and the prediction of established numerical methods this design is expected to be inherently comparable to a full-scale fan concerning performance and instability. The scale of the experimental setup was intentionally chosen as a compromise between physical similarity and the reduction of the investigation costs to enable exhaustive measurements. It is intended to achieve a systemic similarity of Technology Readiness Level 5-6 with largely representative component and environmental test parameters.
Based on the aerodynamic and structural objectives the design shown in the figure has been developed at ECL using elaborate commercial and in-house procedures. The aerodynamic design parameters listed in the table satisfy all demands and objectives laid out above.
This design can be completely opened according to European Open Science procedures. The rotor will consist of 16 carbon fibre blades which are inserted into a metallic disc that is equipped with a telemetry system. This allows the transmission of up to 16 strain gauges applied to the individual blades to continuously monitor and acquire blade vibrations. Downstream of the rotor a stator will be integrated to provide representative outflow conditions. The geometry of the full stage will soon be opened to the research community.
The fan model fulfils the requirements for the desired benchmark test case:
  1. The design parameters are representative for near future low-speed fans with high-subsonic/ low-transonic rotor profiles .
  2. All known similarity parameters affecting aeroelastic and aeroacoustic phenomena are representative for an engine fan (geometry, compressibility, and modal stiffness/damping/shape). Based on current knowledge, the Reynolds Number of the model is sufficiently high to expect a negligible influence on the instability mechanisms.
  3. The academic design has been validated and approved according to recent aerospace standards.
  4. A comparable industrial fan has already been manufactured and successfully tested on the facility in the European Project ENOVAL.

Experiments / Research Strategy

Aeroelastic and Aeroacousic Experiments – PHARE 2

A comprehensive approach is envisaged, fundamentally based on immense synchronized instrumentation. The ground-breaking difference towards conventional research approaches is that the inseparability of the phenomena leading to instability is accepted and it is intended to understand and quantify them in the coupled system. Additionally to the characterization of the instability phenomena, the planned experimental setup will also allow a detailed assessment of the global performance and the emitted noise of the test case, which increases the value for computational method validation. The proposed concept combines complementary measurement systems and enables the detection of interactive mechanisms and instability phenomena where individual systems are insufficient. Unstable aerodynamic phenomena like local flow separations and interactions between shock and tip leakage vortex or boundary layer are sensitive to external feedback mechanisms, either acoustic or structural. It is absolutely necessary to cover all physical contributions synchronously during transient experiments to clearly characterize the coupling mechanism. To achieve this goal it is intended to realize the followng instrumentation concept:
Instrumentation Concept PHARE-2
The anticipated methodology is expected to allow a characterization and quantification of the contributing effects in the stable operating range and during transient onset of instability. A comprehensive approach is envisaged, fundamentally based on immense synchronized instrumentation.
Specifically designed for such a multi-physical investigation, two high-speed test facilities have been commissioned within the EU-Framework-7 programme in 2017 at ECL and proven their suitability for transient experiments.

Sketch of test facility PHARE-2
The core investigation is planned to be conducted on PHARE-2, a 3MW fan test rig with advanced aerodynamic, acoustic and structure-dynamic instrumentation. Aerodynamic, aeroelastic and aeroacoustic investigations including Laser-optical methods will be led by LMFA, complemented by the Von Karman Institute who will participate with advanced unsteady instrumentations, accuracy studies and analysis techniques.

Anechoic Chamber of PHARE-2

Planned Experiments on PHARE-2

Structure-Dynamic Experiments – PHARE 1

To derive isolated mechanical characteristics - particularly exact eigenfrequencies and modal damping - the fan will be analysed on the high speed vacuum facility PHARE-1. Here, the individual blades will be equipped with piezo actuators to excite structural modes. Via strain gauges, the response of the blades can be determined.

PHARE-1 Vacuum Test Rig for Structural Experiments

This rig is dedicated to experimental studies on full scale rotating industrial Fans or Compressor bladed disks at their operating conditions and focusing on the structural dynamics behaviour. Basically the fluid-structure coupling interaction is suppressed as the experiments are performed in vacuum. Also, these conditions allow to drive the specimen using a relatively small amount of power. While aeroelastic excitations are removed, a very versatile piezoelectric excitation system is used for generating vibrations needed for modal testing. The influence on blade response of experiment parameters – namely rotating speed, excitation spectrum, excitation strength and spatial distribution over the fan or compressor - can then be precisely investigated. This research effort is related to several scientific topics: general vibration characterisation of full set of rotating blades involving effects such as stress stiffening, Coriolis, large strains or large displacements vibrations, structural and friction damping. These latter are crucial issues for flutter instability studies where fluid interaction is taken into account after by numerical CFD. The nonlinear analysis of vibrating behaviours induced by friction or contact between parts of the assembly is also a major challenging and need accurate and extensive experimental data required for correlation with solid mechanic numerical computations.

PHARE-1 Vacuum Test Rig for Structural Experiments

One of the major goals of the facility PHARE-1 is to provide such complete and reliable database of experimental results in the field of vibrating and rotating nonlinear structures. The aim is to follow a scientific approach using numerical models compared to experimental data in order to obtain a deeper understanding of physical phenomena involved in such full scale industrial complex structures.
The rig can also serve to demonstrate the efficiency of innovative solutions for reducing vibration levels on the studied test pieces or to evaluate different means of monitoring and measurement technics.
Figure xx depicts a cross sectional view of the test rig. The idea of this test rig is to use an electric motor (650 kW) able to accelerate inertia of full scale test specimen representative of next fan and compressor generations. This is made possible by operating the specimen inside a vacuum chamber extracted by a double stage rotating 630m³/h vane vacuum pump. The driving power is transmitted from the motor up to 8000rpm to the rotating part inside the chamber by means of a rotating seal. The specimen under study is mounted on a supporting rotor whose bearings are lubricated inside the vacuum chamber, oil being returned back from vacuum to the hydraulic unit at ambient pressure.
A telemetry system has been adapted on the driving shaft in order to carry out measurements in the rotating frame and for the alimentation of the piezoelectric actuators. This 44 dynamic strain measurement channels telemetry has the capacity of measuring the 16 blades fan of the CATANA project with very good accuracy and completeness.

Piezo Actuators on carbon blade

Project Organization / Partners

The partners of Project CATANA are the laboratories LMFA and LTDS of Ecole Centrale de Lyon as well as the Von Karman Institute for Fluid Dynamics in Brussels. The project coordination and all aerodynamic and aeroelastic experiments on the fan test facility PHARE-2 / ECL-B3 are conducted by the Turbomachinery Group of LMFA (Coordinators / PIs: Xavier Ottavy and Christoph Brandstetter).

Partners of Project CATANA

ECL LMFA - Laboratoire de Mécanique des Fluides et d'Acoustique UMR CNRS 5509
Ecole Centrale de Lyon (ECL) is one of the leading French public engineering schools which delivers the Engineer Degree of the French Ministry of Education and Research. Two laboratories of ECL participate to Project CATANA:
LMFA develops fundamental and applied research in the fields of transport (aeronautics, space, land and environmental impact), internal aerodynamics, polyphasic flows, urban pollution, aerodynamics and aeroacoustics and turbomachines.
ECL LTDS - Laboratoire de Tribologie et Dynamique des Systèmes UMR CNRS 5513
The LTDS is a multidisciplinary laboratory that conducts research in tribology, mechanics of solids and structures, chemistry and physics of materials, dynamics of systems. Measurements of structural damping of the composite blades are conducted at the vacuum test facility PHARE-1 of LTDS (Resp. Claude Gibert)
VKI - The Von Karman Institute for Fluid Dynamics
Advanced Probe measurements will be performed by the Von Karman Institute for Fluid Dynamics (VKI), founded in 1956, which is an international non-profit organization for post graduate education and research (Resp. Fabrizio Fontaneto).
In the frame of CATANA, VKI will be in charge of delivering an as-complete-as-possible characterization of turbulence, both upstream and downstream the test section. At such extent, VKI will design, machine and operate up to 4 multi-sensor hot wire probes.
Furthermore, VKI will contribute to CATANA with its last developments in terms of uncertainty analysis.


Christoph Brandstetter
École Centrale de Lyon
Laboratoire de Mécanique des Fluides et d'Acoustique
36 avenue Guy de Collongue
69134 Ecully Cedex
tel : +33 (0)


Coupling Mechanisms and Instability

[1] Christoph BRANDSTETTER, Benoit PAOLETTI, Xavier OTTAVY. Compressible Modal Instability Onset in an Aerodynamically Mistuned Transonic Fan. ASME. J. Turbomach. 2018;():. doi:10.1115/1.4042310
[2] Pierre DUQUESNE, Q. RENDU, S. AUBERT, P. FERRAND. Choke flutter instability sources tracking with linearized calculations. International Journal of Numerical Methods for Heat & Fluid Flow (2018). DOI 10.1108/HFF-06-2018-0281
[3] Christoph BRANDSTETTER, Valdo PAGES, Pierre DUQUESNE, Benoit PAOLETTI, Stephane AUBERT, Xavier OTTAVY. (2018). Project PHARE-2 - a High-Speed UHBR Fan Test Facility for a new Open-Test-Case. 15th International Symposium on Unsteady Aerodynamics, Aeroacoustics & Aeroelasticity of Turbomachines, Oxford, UK
[4] Anne-Lise FIQUET, Christoph BRANDSTETTER, Stephane AUBERT, S., Mickael PHILIT. (2018). Non-Engine Order Oscillations in an Axial Multi-Stage Compressor - Acoustic Resonance. 15th International Symposium on Unsteady Aerodynamics, Aeroacoustics & Aeroelasticity of Turbomachines, Oxford,UK
[5] Pierre DUQUESNE, S. AUBERT, Q. RENDU, P. FERRAND. Effect of nodal diameter on the local blades vibration on the choke flutter instability in transonic UHBR fan. 15th International Symposium on Unsteady Aerodynamics, Aeroacoustics & Aeroelasticity of Turbomachines. University of Oxford, UK, September 2018
[6] Pierre DUQUESNE, S. AUBERT, Q. RENDU, P. FERRAND. Effect of frozen turbulence assumption on the local blades vibration on the choke flutter instability in transonic UHBR fan. IUTAM Symposium on Critical flow dynamics involving moving/deformable structures with design applications. Santorini, Greece, June 2018
[7] Pierre DUQUESNE, Q. RENDU, P. FERRAND, S. Aubert. Local contribution of blades vibration on the choke flutter instability in transonic UHBR fan. 53rd 3AF International Conference on Applied Aerodynamics: Multiphysics approach in Aerodynamics. Salon-de-Provence, France, 2018
[8] Victor MOËNNE-LOCCOZ, Isabelle TRÉBINJAC, Emmanuel BENICHOU, Sébastien GOGUEY, Benoît PAOLETTI, Pierre LAUCHER (2017). An experimental description of the flow in a centrifugal compressor from alternate stall to surge. J. Therm. Sci. 26, 289–296. doi:10.1007/s11630-017-0941-8
[9] Johannes SCHREIBER, Benoît PAOLETTI, Xavier OTTAVY (2017). Observations on rotating instabilities and spike type stall inception in a high-speed multistage compressor. Int. J. Rot. Machin. 2017, 7035870 (11 pages). doi:10.1155/2017/7035870
[10] Yannick BOUSQUET, Nicolas BINDER, Guillaume DUFOUR, Xavier CARBONNEAU, Isabelle TRÉBINJAC, Mathieu ROUMEAS (2016). Numerical investigation of Kelvin-Helmholtz instability in a centrifugal compressor operating near stall. J. Turbomach. 138, 071007 (9 pages). doi:10.1115/1.4032457
[11] Flore CREVEL, Nicolas GOURDAIN, Xavier OTTAVY (2014). Numerical simulation of aerodynamic instabilities in a multistage high-speed high-pressure compressor on its test rig - Part II: deep surge. J. Turbomach. 2014, 101004 (15 pages). doi:10.1115/1.4027968
[12] Flore CREVEL, Nicolas GOURDAIN, Stéphane MOREAU (2014). Numerical simulation of aerodynamic instabilities in a multistage high-speed high-pressure compressor on its test-rig - Part I : rotating stall. J. Turbomach. 136, 101003 (14 pages). doi:10.1115/1.4027967
[13] Nicolas COURTIADE, Xavier OTTAVY (2013). Experimental study of surge precursors in a high-speed multistage compressor. J. Turbomach. 135, 061018 (9 pages). doi:10.1115/1.4023462
[14] Nicolas COURTIADE, Xavier OTTAVY (2013). Study of the acoustic resonance occurring in a multistage high-speed axial compressor. Proc. IMechE Part A, J. Power Energy 227, 654–664. doi:10.1177/0957650913500493
[15] Nicolas COURTIADE, Xavier OTTAVY, Nicolas GOURDAIN (2012). Modal decomposition for the analysis of the rotor-stator interactions in multistage compressors. J. Therm. Sci. 21, 276–285. doi:10.1007/s11630-012-0545-2
[16] Nicolas GOURDAIN, Fabien WLASSOW, Xavier OTTAVY (2012). Effect of tip clearance dimensions and control of unsteady flows in a multi-stage high-pressure compressor. J. Turbomach. 134, 051005 (13 pages). doi:http://dx.doi.org/10.1115/1.4003815
[17] Xavier OTTAVY, Nicolas COURTIADE, Nicolas GOURDAIN (2012). Experimental and Computational Methods for Flow Investigation in High-Speed Multistage Compressor. J. Propul. Power 28, 1141–1155. doi:10.2514/1.60562
[18] Nicolas GOURDAIN, S. BURGUBURU, Francis LEBOEUF, G.J. MICHON (2010). Simulation of rotating stall in a whole stage of an axial compressor. Comput. Fluids 39, 1644–1655. doi:10.1016/j.compfluid.2010.05.017
[19] Guillaume LEGRAS, Nicolas GOURDAIN, Isabelle TRÉBINJAC (2010). Numerical analysis of the tip leakage flow field in a transonic axial compressor with circumferential casing treatment. J. Therm. Sci. 19, 198–205. doi:10.1007/s11630-010-0198
[20] Nicolas BULOT, Isabelle TRÉBINJAC (2009). Effect of the unsteadiness on the diffuser flow in a transonic centrifugal compressor stage. Int. J. Rot. Machin. 2009, 932593 (11 pages). doi:10.1155/2009/932593
[21] Nicolas BULOT, Isabelle TRÉBINJAC, Xavier OTTAVY, Pascale KULISA, G. HALTER, Benoît PAOLETTI, Patrick KRIKORIAN (2009). Experimental and numerical investigation of the flow field in a high-pressure centrifugal compressor impeller near surge. Proc. IMechE Part A, J. Power Energy 223, 657–666. doi:10.1243/09576509JPE817
[22] Nicolas GOURDAIN, Francis LEBOEUF (2009). Unsteady simulation of an axial compressor stage with casing and blade passive treatments. J. Turbomach. 131, 021013 (12 pages). doi:10.1115/1.2988156
[23] Isabelle TRÉBINJAC, Pascale KULISA, Nicolas BULOT, Nicolas ROCHUON (2009). Effect of unsteadiness on the performance of a transonic centrifugal compressor stage. J. Turbomach. 131, 041011 (9 pages). doi:10.1115/1.3070575
[24] Nicolas ROCHUON, Isabelle TRÉBINJAC, Pascale KULISA, G. BILLONNET (2008). Assessment of jet-wake flow structures induced by three-dimensional hub wall contouring. IREME 2, 113–121
[25] Nicolas BULOT, Isabelle TRÉBINJAC (2007). Impeller-diffuser interaction: analysis of the unsteady flow structures based on their direction of propagation. J. Therm. Sci. 16, 193–202. doi:10.1007/s11630-007-0193-0
[26] Isabelle TRÉBINJAC, Nicolas ROCHUON, G. BILLONNET (2006). An extraction of the dominant rotor-stator interaction modes by the use of Proper Orthogonal Decomposition (POD). J. Therm. Sci. 15, 109–114. doi:10.1007/s11630-006-0109-4
[27] Nicolas GOURDAIN, S. BURGUBURU, Francis LEBOEUF, H. MILTON (2006). Numerical simulation of rotating stall in a subsonic compressor. Aerosp. Sci. Technol. 10, 9–18. doi:10.1016/j.ast.2005.07.006
[28] Isabelle TRÉBINJAC, D. CHARBONNIER, Francis LEBOEUF (2005). Unsteady rotor-stator interaction in high speed compressor and turbine stages. J. Therm. Sci. 14, 289–297. doi:10.1007/s11630-005-0047-6
[29] Isabelle TRÉBINJAC, C. VIXEGE (2002). Experimental analysis of the rotor stator interaction within a high pressure centrifugal compressor. J. Therm. Sci. , 1–9. doi:10.1007/s11630-002-0014-4
[30] Xavier OTTAVY, Isabelle TRÉBINJAC, André VOUILLARMET (2001). Analysis of the inter-row flow field within a transonic axial compressor : Part 2 - Unsteady flow analysis. J. Turbomach. 123, 57–63. doi:10.1115/1.1328086
[31] Xavier OTTAVY, Isabelle TRÉBINJAC, André VOUILLARMET (2001). Analysis of the inter-row flow field within a transonic axial compressor : Part 1 - Experimental investigation. J. Turbomach. 123, 49–56. doi:10.1115/1.1328085
[32] BRANDSTETTER, C., JÜNGST, M., & SCHIFFER, H.-P. (2017). Measurements of Radial Vortices, Spill Forward and Vortex Breakdown in a Transonic Compressor. ASME. Journal of Turbomachinery. 140(6):061004 . doi: 10.1115/1.4039053
[33] BRANDSTETTER, C., & SCHIFFER, H.-P. (2017). PIV Measurements of the Transient Flow Structure in the Tip Region of a Transonic Compressor Near Stability Limit. Journal of the Global Power and Propulsion Society, doi: 10.22261/JGPPS.JYVUQD
[34] BRANDSTETTER, C., WARTZEK, F., WERNER, J., SCHIFFER, H.-P., & HEINICHEN, F. (2016). Unsteady Measurements of Periodic Effects in a Transonic Compressor With Casing Treatments. ASME. Journal of Turbomachinery, 138(5):051007. doi:10.1115/1.4032185
[35] BRANDSTETTER, C., HOLZINGER, F., SCHIFFER, H.-P., STAPELFELDT, S., & VAHDATI, M. (2016). Near Stall Behavior of a Transonic Compressor Rotor with Casing Treatment. ASME. Turbo Expo: Power for Land, Sea, and Air, Volume 2D: Turbomachinery: V02DT44A013., GT2016-56606. doi:10.1115/gt2016-56606
[36] BRANDSTETTER, C., KEGALJ, M., WARTZEK, F., HEINICHEN, F., & Schiffer, H.-P. (2014).Stereo PIV Measurement of Flow Structures underneath an Axial-Slot Casing Treatment on a One and a Half Stage Transonic Compressor. 17th International Symposium on Applications 2014, Lisbon, Portugal
[37] BRANDSTETTER, C., BIELA, C., KEGALJ, M., & SCHIFFER, H.-P. (2011). PIV-Measurements in a Transonic Compressor Test Rig with Variable Inlet Guide Vanes. Proceedings of 20th ISABE 2011, Gothenburg, Sweden

Analysis of individual phenomena in turbomachinery (ECL-LMFA)

[38] Feng GAO, Wei MA, Jinjing SUN, Jérôme BOUDET, Xavier OTTAVY, Yangwei LIU, Lipeng LU, Liang SHAO (2017). Parameter study on numerical simulation of corner separation in LMFA-NACA65 linear compressor cascade. Chin. J. Aeronauti. 30, 15–30. doi:10.1016/j.cja.2016.09.015
[39] Hongwei MA, Wei WEI, Xavier OTTAVY (2017). Experimental investigation of flow field in a laboratory-scale compressor Chin. J. Aeronauti. 30, 31–46. doi:10.1016/j.cja.2016.09.016
[40] Gherardo ZAMBONINI, Xavier OTTAVY, Jochen KRIEGSEIS (2017). Corner separation dynamics in a linear compressor cascade. J. Fluids Eng. 139, 061101 (13 pages). doi:10.1115/1.4035876
[41] Jérôme BOUDET, Joëlle CARO, Bo LI, Emmanuel JONDEAU, Marc C. JACOB (2016). Zonal large-eddy simulation of a tip leakage flow. Int. J. Aeroacoustics 15, 646–661. doi:10.1177/1475472X16659215
[42] Jérôme BOUDET, Adrien CAHUZAC, Philip KAUSCHE, Marc C. JACOB (2015). Zonal large-eddy simulation of a fan tip-clearance flow, with evidence of vortex wandering. J. Turbomach. 137, 061001 (9 pages). doi:10.1115/1.4028668
[43] Feng GAO, Wei MA, Gherardo ZAMBONINI, Jérôme BOUDET, Xavier OTTAVY, Lipeng LU, Liang SHAO (2015). Large-eddy simulation of 3-D corner separation in a linear compressor cascade. Phys. Fluids 27, 085105 (21 pages). doi:10.1063/1.4928246
[44] Feng GAO, Gherardo ZAMBONINI, Jérôme BOUDET, Xavier OTTAVY, Lipeng LU, Liang SHAO (2015). Unsteady behavior of corner separation in a compressor cascade: Large eddy simulation and experimental study. Proc. IMechE Part A, J. Power Energy 229, 508–519. doi:10.1177/0957650915594314
[45] Mehmet MERSINLIGIL, Jean-François BROUCKAERT, Nicolas COURTIADE, Xavier OTTAVY (2013). On using fast response pressure sensors in aerodynamic probes to measure total temperature and entropy generation in turbomachinery blade rows. J. Eng. Gas Turbine Power 135, 101601 (10 pages). doi: 10.1115/1.4024999
[46] Wei MA, Xavier OTTAVY, Lipeng LU, Francis LEBOEUF (2013). Intermittent corner separation in a linear compressor cascade. Exp. Fluids 54, 1–17. doi:10.1007/s00348-013-1546
[47] Julien MARTY, Lionel CASTILLON, J.-C. BONIFACE, S. BURGUBURU, Antoine GODARD (2013). Numerical and experimental investigations of flow control in axial compressors. Aerospace Lab Journal 6, 1–13
[48] William RIÉRA, Lionel CASTILLON, Julien MARTY, Francis LEBOEUF (2013). Inlet condition effects on the tip clearance flow with zonal detached eddy simulation. J. Turbomach. 136, 041018 (10 pages). doi:10.1115/1.4025216
[49] Mehmet MERSINLIGIL, Jean-François BROUCKAERT, Nicolas COURTIADE, Xavier OTTAVY (2012). A high temperature high bandwidth fast response total pressure probe for measurements in a multistage axial compressor. J. Eng. Gas Turbine Power 134, 061601. doi:10.1115/1.4006061
[50] Wei MA, Xavier OTTAVY, Lipeng LU, Francis LEBOEUF, Feng GAO (2011). Experimental study of corner stall in a linear compressor cascade. Chin. J. Aeronauti. 24, 235–242. doi:10.1016/S1000-9361(11)60028-9
[51] Nicolas BULOT, Xavier OTTAVY, Isabelle TRÉBINJAC (2010). Unsteady pressure measurements in a high-speed centrifugal compressor. J. Therm. Sci. 19, 1–8. doi:10.1007/s11630-010-0000-0
[52] Xavier OTTAVY, Isabelle TRÉBINJAC, André VOUILLARMET (1998). Treatment of L2F anemometer measurement volume distortions created by curved windows for turbomachinery application. Meas. Sci. Technol. 9, 1511–1521. doi:10.1088/0957-0233/9/9/021.

Structure Dynamics (ECL-LTDS)

[1] MABILIA A., GIBERT C., THOUVEREZ F., DE JAEGHERE E., SANCHEZ L., GIOVANNONI L., 2018, Modal Testing of a Full-Scale Rotating Woven Composite Fan Using Piezoelectric Excitation, 10th International Conference on Rotor Dynamics , 23/09/2018 - 27/09/2018, Rio de Janeiro - Brésil, oral, acte : Proceedings of the 10th International Conference on Rotor Dynamics – IFToMM, ISBN 978-3-319-99269-3, Springer International Publishing, 62, 291-305.
[2] MABILIA A., GIBERT C., THOUVEREZ F., De JAEGHERE E., 2018, Nonlinear Forced Response of a Composite Fan Blade Actuated by Piezoelectric Patches: Simulation and Testing, Nonlinear Dynamics, 1, 351-362.
[3] DUMARTINEIX C., CHOUVION B., THOUVEREZ F., Parent M.-O., 2018, An Efficient Approach for the Frequency Analysis of Non-Axisymmetric Rotating Structures: Application to a Coupled Bladed Bi-Rotor System, Journal of Engineering for Gas Turbines and Power, 1, 1-12.
[4] ALMEIDA P., GIBERT C., THOUVEREZ F., LEBLANC X., OUSTY J.-P., 2016, Numerical analysis of bladed disk-casing contact with friction and wear, Journal of Engineering for Gas Turbines and Power, 138, 12, 1-12.
[5] JOANNIN C., THOUVEREZ F., CHOUVION B., OUSTY J.-P., 2015, Nonlinear Modal Analysis of Mistuned Periodic Structures Subjected to Dry Friction, Journal of Engineering for Gas Turbines and Power, 138, 7, 1-17.
[6] THOUVEREZ F., GROLET A., GIBERT C., 2014, Non-linear periodic solutions of bladed disks, EURODYN 2014 9th International Conference on Structural Dynamics, 30/06/2014 - 02/07/2014, Porto - Portugal, oral, acte : Proceedings 9th International Conference on Structural Dynamics, 12 pages.
[7] ALMEIDA P., GIBERT C., LEBLANC X., OUSTY J.-P., THOUVEREZ F., 2012, Experimental and Numerical Investigations on a Rotating Centrifugal Compressor, ASME Gas Turbine Technical Congress & Exposition 2012, 09/11/2012 - 15/11/2012, Houston-États-Unis, oral, acte : ASME Gas Turbine Technical Congress & Exposition 2012, ISBN 978-0-7918-4520-2, 7, 1133-1142.
[8] PAYER F., FERRAND P., DUGEAI A., THOUVEREZ F., 2012, Comparison of Fluid-Structure Coupling Methods for Blade Forced Response Prediction, ASME 2012 Gas Turbine India Conference, 01/12/2012 - 01/12/2012, Maharashtra - Inde, oral, acte : ASME 2012 Gas Turbine India Conference, 595-602.
[9] GIBERT C., BLANC L., ALMEIDA P., LEBLANC X., OUSTY J.-P., Thouverez F., Lainé J.-P., 2012, Modal Tests and Analysis of a Radial Impeller at Rest: Influence of Surrounding Air on Damping, ASME Gas Turbine Technical Congress & Exposition 2012, 11/06/2012 - 15/06/2012, Copenhague - Danemark, oral, acte : ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, 1121-1131.
[10] GIBERT C., KHARYTON V., THOUVEREZ F., JEAN P., 2010, On forced response of a rotating integrally bladed disk: Predictions and experiments, ASME Gas Turbine Technical Congress & Exposition 2010, 14/06/2010 - 18/06/2010, Glasgow - Royaume-Uni, oral, acte : Proceedings of ASME Turbo Expo: Power for Land, Sea and Air 2010, 6, 1103-1116.
[11] LAXALDE D., THOUVEREZ F., 2009, Complex Non-Linear Modal Analysis for Mechanical Systems: Application to Turbomachinery Bladings With Friction Interfaces, Journal of Sound and Vibration, 322, 4, 1009-1025.
[12] PICHOT F., LAXALDE D., SINOU J.J., THOUVEREZ F., LOMBARD J.P., “Mistuning identification for industrial blisks based on the based achievable eigenvector”, Computers & Structures, 84, 2033-2049, 2006.

Measurement Techniques / Uncertainty (VKI)

[1] BOUFIDI E., “On the Dynamic Response of Constant Temperature Hot Wire Anemometers (CTHWA)”, Symposium of VKI PhD Research 2018
[2] BOUFIDI E., COTTES M., FONTANETO F., “CTHWA dynamic response effects on turbulence measurements in turbomachinery flows”, XXIV Biannual Symposium on Measuring Techniques in Turbomachinery, Prague 29 - 31 August 2018
[3] BOUFIDI E., ALATI M., FONTANETO F., LAVAGNOLI S., “Design and testing of a miniaturized five-hole fast-response pressure probe with large frequency bandwidth and high angular sensitivity”, Proceedings of ASME Turbo Expo 2019, June 17 - 21, 2019 in Phoenix, Arizona USA
[4] BOUFIDI E., “Uncertainty Quantification of Turbulence Statistics Measured by Hot-Wire Anemometry”, Symposium of VKI PhD Research 2017
[5] BOUFIDI, E., LAVAGNOLI, S., FONTANETO, F., “A probabilistic uncertainty estimation method for turbulence parameters measured by hot-wire anemometry in short duration wind tunnels”, Proceedings of ASME Turbo Expo 2019, June 17 - 21, 2019 in Phoenix, Arizona USA
[6] J.-F. BROUCKAERT, M. MERSINLIGIL, and M. PAU, “A Conceptual Design Study for a New High Temperature Fast Response Cooled Total Pressure Probe,” J. Eng. Gas Turbines Power, vol. 131, no. 2, pp. 021602-021602-12, 2008.
[7] B. CUKUREL, S. ACARER, and T. ARTS, “A novel perspective to high-speed cross-hot-wire calibration methodology,” Exp Fluids, vol. 53, no. 4, pp. 1073–1085, 2012.
[8] F. FONTANETO, T. ARTS, M. SIMON, and P. PICOT, “Aerodynamic Performance of an Ultra-Low Aspect Ratio Centripetal Turbine Stator,” International Journal of Turbomachinery, Propulsion and Power, vol. 1, no. 1, p. 3, 2016.
[9] V. ILIOPOULOU and T. ARTS, “The dual thin-film probe for high-frequency flow temperature measurements,” Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, vol. 219, no. 6, pp. 461–469, 2005.
[10] S. LAVAGNOLI, C. De MAESSCHALCK, and V. ANDREOLI, “Design Considerations for Tip Clearance Control and Measurement on a Turbine Rainbow Rotor With Multiple Blade Tip Geometries,” Journal of Engineering for Gas Turbines and Power, vol. 139, no. 4, p. 042603, 2017.
[11] S. LAVAGNOLI, C. DE MAESSCHALCK, and G. PANIAGUA, “Uncertainty analysis of adiabatic wall temperature measurements in turbine experiments,” Applied Thermal Engineering, vol. 82, pp. 170–181, 2015.
[12] S. LAVAGNOLI, G. PANIAGUA, M. TULKENS, and A. STEINER, “High-fidelity rotor gap measurements in a short-duration turbine rig,” Mechanical Systems and Signal Processing, vol. 27, pp. 590–603, 2012.
[13] M. MERSINLIGIL, J.-F. BROUCKAERT, N. COURTIADE, and X. OTTAVY, “A High Temperature High Bandwidth Fast Response Total Pressure Probe for Measurements in a Multistage Axial Compressor,” J. Eng. Gas Turbines Power, vol. 134, no. 6, pp. 061601-061601-11, 2012.
[14] C. H. SIEVERDING, T. Arts, R. DÉNOS, and J.-F. BROUCKAERT, “Measurement techniques for unsteady flows in turbomachines,” Experiments in Fluids, vol. 28, no. 4, pp. 285–321, 2000.
[15] J. F. L. SOUSA, S. LAVAGNOLI, G. PANIAGUA, and L. VILLAFAÑE, “Three-dimensional (3D) inverse heat flux evaluation based on infrared thermography,” Quantitative InfraRed Thermography Journal, vol. 9, no. 2, pp. 177–191, 2012.
[16] T. YASA, G. PANIAGUA, and R. DÉNOS, “Application of Hot-Wire Anemometry in a Blow-Down Turbine Facility,” J. Eng. Gas Turbines Power, vol. 129, no. 2, pp. 420–427, 2006.

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