Blackbox Optimization for Aircraft Engine Blades With Contact Interfaces

Lainé, Julien; Piollet, Elsa; Nyssen, Florence; Batailly, Alain

doi:10.1115/1.4042808

Cited by 7 publications

(12 citation statements)

References 31 publications

(68 reference statements)

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“…It is important to note, however, that the reduction is particularly striking for the first torsion mode, while interactions seem to occur mainly with the first bending mode. This confirms recent results showing that an efficient improvement of the blade's robustness may involve taking into account the dynamic clearance of more modes than only the first bending mode [56].…”

Section: Dynamic Clearancesupporting

confidence: 91%

“…The geometry of the reference blade can be modified either by acting on the MCA parameters of each profile, or by modifying the stacking line along which the profiles are positioned by varying the sweep and lean of the blade. Previous works have shown that modifying the stacking line has significant consequences on the aerodynamic performances of the blade [31,54,55] as well as on the blade's response to contact events [38,56]. Therefore, six new blades are defined by varying the sweep and lean to compare their responses to contact events with that of the reference blade.…”

Section: Re-designed Blades With Sweep and Lean Variationsmentioning

confidence: 99%

“…Previous works have shown a relationship between a blade's robustness to contact events and its dynamic clearance, studied in details in [56] and investigated previously as the "clearance consumption" in [59]. The dynamic clearance quantifies the variation of the radial position of a given point on the blade tip as the blade vibrates along one of its free-vibration modes: large dynamic clearance means that vibration along the mode modifies significantly the blade/casing clearance.…”

Section: Dynamic Clearancementioning

confidence: 99%

“…The dynamic clearance quantifies the variation of the radial position of a given point on the blade tip as the blade vibrates along one of its free-vibration modes: large dynamic clearance means that vibration along the mode modifies significantly the blade/casing clearance. Designing blades with reduced dynamic clearances on one or more of their modes is one avenue currently investigated to design blades robust to contact interactions [56]. For all seven blades, the dynamic clearance c d at the leading edge is plotted in Figs.…”

Section: Dynamic Clearancementioning

confidence: 99%

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Blade/casing rubbing interactions in aircraft engines: Numerical benchmark and design guidelines based on NASA rotor 37

Piollet

Nyssen

Batailly

2019

Journal of Sound and Vibration

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Blade/casing rubbing interactions in aircraft engines: Numerical benchmark and design guidelines based on NASA rotor 37. Journal of Sound and Vibration, Elsevier, 2019, 460, pp.Abstract In order to improve the efficiency of aircraft engines, the reduction of clearances between blade tips and their surrounding casing is one avenue manufacturers consider to lower aerodynamic losses. This reduction increases the risk of blade tip/casing contact interactions under nominal operating conditions. Designers need tools to accurately predict subsequent nonlinear vibrations. Engineers and researchers have developed a variety of sophisticated numerical models to predict blades' responses. These models are related to distinct frameworks (time/frequency domain) and various solution algorithms (explicit/implicit time integration schemes, penalty/Lagrange multiplier contact treatment...) which calls for comparative analyses. However, published results are often limited for the sake of confidentiality thus preventing any detailed confrontation. While qualitative understanding can be gained from simplified academic models, full scale models are needed to predict complex interactions in a realistic manner. In this context, this paper proposes a benchmark featuring detailed simulations and analyses of a full 3D finite element model based on the open NASA rotor 37 compressor blade to facilitate reproducibility and collaboration across the research community. NASA rotor 37, a compressor stage widely used as a test case in aerodynamic simulations and validations, has the advantage of presenting a realistic blade geometry. The geometry of the blade is built from publicly available reports. The paper provides details on the geometry, the numerical model and the results to allow an easy use of this model across the fields of structural dynamics. Two contact scenarios are investigated: one with direct contact against the casing, and one with abradable material deposited on the casing to mitigate contact severity through wear. The nonlinear vibration response of the blade is simulated in the time domain. It is evidenced that the addition of the abradable material decreases the amplitude of vibration for most of the angular speeds investigated. However, new interactions appear for some angular speeds. The obtained results are consistent with previous simulations on industrial geometries. Based on works showing improved aerodynamic performances when the blade is tilted, a total of seven geometries are investigated: the reference blade, with a straight vertical stacking line similar to the original rotor 37, two forward-leaned blades, two backward-swept blades and two full forward chordwise swept blades. The sweep and lean variations are shown to have a dramatic impact on the vibration response: the backward sweep results in an increased blade's robustness to contact events and the full forward chordwise sweep in a reduced robustness, while the forward lean leads to a robustness similar to the reference blade. RésuméLa réduction des jeux au...

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Section: Dynamic Clearancesupporting

confidence: 91%

Section: Re-designed Blades With Sweep and Lean Variationsmentioning

confidence: 99%

Section: Dynamic Clearancementioning

confidence: 99%

Section: Dynamic Clearancementioning

confidence: 99%

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Blade/casing rubbing interactions in aircraft engines: Numerical benchmark and design guidelines based on NASA rotor 37

Piollet

Nyssen

Batailly

2019

Journal of Sound and Vibration

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“…In particular, the blade was optimized with respect to its clearance consumption [17]-which quantifies how the blade-tip/casing clearance evolves as the blade vibrates along one of its free-vibration modes-and much lower amplitudes of vibration were numerically predicted for the redesigned blade. Based on this work, a blade parameterization was later proposed for academic blade models and systematic optimization of these profiles with respect to their clearance consumption underlined the relevance of this criterion [18].…”

Section: Introductionmentioning

confidence: 99%

Methodology for the Redesign of Compressor Blades Undergoing Nonlinear Structural Interactions: Application to Blade-Tip/Casing Contacts

Kojtych

Nyssen

Audet

et al. 2022

Journal of Engineering for Gas Turbines and Power

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Over the past decade, the drive towards more efficient aircraft engines has pushed the boundaries of operating ranges far beyond a linear structural context. Nonlinear interfaces, such as blade-tip/casing contacts, are to be expected in nominal operating conditions. However, current blade design methodologies still rely on empirical structural considerations, often linear, which may lead to costly redesign operations. This work aims at proposing a methodology for the redesign of blades undergoing nonlinear structural interactions. A three-step redesign process is considered: (1) parameterization of an existing blade, (2) update of blade parameters with respect to a surrogate performance criterion and (3) performance check of the optimized blade. An original two-way parameterization method is proposed to parameterize existing blades and generate models from blade parameters. As a proof-of-concept, the redesign of the NASA compressor blade rotor 37 and fan blade rotor 67 with respect to blade-tip/casing contacts is considered. High-fidelity parameterized models of the initial blades are obtained and their dynamic response to contact interactions are analyzed. Geometries are updated with respect to their clearance consumption, as its minimization has shown beneficial effects on the considered contact interactions. The proposed methodology allows to better assess the relevance of this performance criterion in the context of blade-tip/casing contacts.

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