Project PHARE-2—A High-Speed UHBR Fan Test Facility for a New Open-Test Case

Brandstetter, Christoph; Pagès, Valdo; Duquesne, Pierre; Paoletti, Benoît; Aubert, Stéphane; Ottavy, Xavier

doi:10.1115/1.4043883

Cited by 21 publications

(19 citation statements)

References 9 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Aeroelastic tests have been conducted on the test facility ECL-B3/PHARE-2 of Ecole Centrale de Lyon [27], schematically shown in Fig. 3.…”

Section: Test Case: Enoval Low-speed Fanmentioning

confidence: 99%

“…In addition to the high-speed core compressor (hub-to-tip ratio ∼ 0.5) the model has been validated for the low-speed transonic fan described in this study (hub-to-tip ratio << 0.5, experiment) [28], the Open-Test-Case fan ECL5/CATANA (hub-to-tip ratio ∼ 0.3, numerics) [27], and a transonic booster (ENOVAL, hub-to-tip ratio > 0.5, experiment and numerics). Its general applicability indicates that the physical phenomenon, which is limited to the outer section of the rotor (> 90% span) [19] is independent of the hub-to-tip ratio.…”

Section: Model Descriptionmentioning

confidence: 99%

“…By setting the blade vibration frequency (EO R =ω R v /Ω S r = 1911Hz/249Hz = 7.67), blade number (27) and propagation speed to the values given in [4], the NSV model described above develops the spectrum presented in Fig. 13b.…”

Section: Transonic Fanmentioning

confidence: 99%

See 2 more Smart Citations

Interpretation of Stall Precursor Signatures

Brandstetter

Ottavy

Paoletti

et al. 2021

Journal of Turbomachinery

Self Cite

View full text Add to dashboard Cite

A specific phenomenon that has been observed in many experimental studies on turbomachinery compressors and fans is discussed under the term ‘rotating instabilities’. It is associated to a local aerodynamic phenomenon, typically occurring in the tip region at highly loaded near stall conditions and often linked to blade vibrations. Even though the effect has been discussed over more than two decades, a very ambiguous interpretation still prevails. A particular problem is that certain signatures in measurement data are often considered to characterize the phenomenon despite possible misinterpretations. The present paper illustrates that a specific image of a pulsating disturbance that has been established in the 1990s needs to be reconsidered. At the example of a recent investigation on a composite fan the difficulties concerning sensor placement and post-processing techniques is discussed with a focus on spectral averaging, isolation of non-synchronous phenomena and multi-sensor cross-correlation methods.

show abstract

“…Aeroelastic tests have been conducted on the test facility ECL-B3/PHARE-2 of Ecole Centrale de Lyon [27], schematically shown in Fig. 3.…”

Section: Test Case: Enoval Low-speed Fanmentioning

confidence: 99%

Section: Model Descriptionmentioning

confidence: 99%

See 1 more Smart Citation

Interpretation of Stall Precursor Signatures

Brandstetter

Ottavy

Paoletti

et al. 2021

Journal of Turbomachinery

Self Cite

View full text Add to dashboard Cite

show abstract

“…The test facility ECL-B3 stands as an innovative, novel, multi-physical test rig designed and built in cooperation between Ecole Centrale de Lyon and Safran Aircraft Engines through the ANR-EQUIPEX program. This test rig is designed to host fan architectures representative of modern UHBR stages at scales between 1:4 and 1:3 [12]. The tested vehicle in this study was designed by Safran AE and is a technology demonstrator of a next generation UHBR stage.…”

Section: Test Facility Ecl-b3mentioning

confidence: 99%

Aerodynamic Investigation of a Composite Low-Speed Fan for UHBR Application

Rodrigues

Soulat

Paoletti

et al. 2021

Journal of Turbomachinery

Self Cite

View full text Add to dashboard Cite

A composite fan stage representative of a modern UHBR architecture has been investigated experimentally on a novel test facility at Ecole Centrale de Lyon. These measurements show indications for strong overloading of the tip region resulting in extensive blockage of the blade passage. The performance of the fan is analyzed with extensive instrumentation including radial profiles upstream and downstream of the rotor. Unsteady pressure measurements help to interpret the flow structure in the tip region. The results are presented across a range of operating points on the design speedline. At the stability limit, the machine suffers from Non-Synchronous Vibrations which result from small scale aerodynamic disturbances propagating between the leading edges. A detailed analysis on the occurring waveforms is presented for two operating speeds. In order to further analyze the observed phenomena, a numerical study has been conducted using the RANS solver elsA. The results of steady calculations are discussed in comparison with the detailed experiments. Unsteady simulations near the stability limit accurately predict the aerodynamic disturbances observed during NSV. The obtained results are unusual for typical state-of-the-art transonic fans, as they show the same behavior as high-pressure compressor front stages, dominated by blockage caused by tip leakage flow. Even though flutter is not observed, the observed Non-Synchronous Vibration mechanism is a critical aeroelastic phenomenon which is of great interest for future designs of low speed fans.

show abstract

“…The first assumption is widely accepted in the community since turbomachinery blades are usually made of titanium/nickel-based alloys, which are known for their excellent stiffness-to-weight ratio. However, modern gas turbine architecture has the tendency to make more use of the composite material [5]. The low mass ratio configuration has been reported to cause unusual aeroelastic phenomena in the literature due to the stronger coupling between the fluid flow and the structural dynamics.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Structurally and Aerodynamically Mistuned Oscillating Cascade Using Fully Coupled Method

Phan

2021

Journal of Engineering for Gas Turbines and Power

View full text Add to dashboard Cite

There seems to be a lack of clear and systematic understanding of physical behaviour and mechanisms of mistuned bladerows, particularly in the context of the aerodynamic mistuning versus the structural (frequency) mistuning. A high-fidelity fully-coupled method is desirable to investigate the vibration characteristics of aeroelasticity problems with strong fluid-structure interaction effects, as well as blade mistuning effects. In the present work, the direct nonlinear time-domain fully-coupled method is adopted to investigate the dynamics mechanism of a mistuned oscillating cascade. The main objectives are two-folds, firstly to elucidate the basic vibration characteristics of a mistuned bladerow, and secondly to examine the aeroelastic effects of mistuning. Three conditions of interest are considered: a) the structural mistuning only, b) the aerodynamic mistuning only, and c) a combination of the two. The present results show that firstly a mistuned configuration tends to vibrate with the same frequency and a predominantly constant inter-blade phase-angle. Vibration amplitudes of the blades vary significantly with a strong mode localization effect for the structural mistuning. For the concurrent structural-aerodynamic mistuning, the localization is stronger than in the standalone structural mistuning case. Secondly, a monotonic increase of the aeroelastic stability with the structural mistuning magnitude is observed. On the other hand, the aerodynamically mistuned cascade shows a stabilizing effect with a small amount of mistuning but exhibits a destabilizing effect with a large mistuning. Furthermore... see paper for the full abstract

show abstract

Project PHARE-2—A High-Speed UHBR Fan Test Facility for a New Open-Test Case

Cited by 21 publications

References 9 publications

Interpretation of Stall Precursor Signatures

Interpretation of Stall Precursor Signatures

Aerodynamic Investigation of a Composite Low-Speed Fan for UHBR Application

Investigation of Structurally and Aerodynamically Mistuned Oscillating Cascade Using Fully Coupled Method

Contact Info

Product

Resources

About