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            <title xml:lang="en">Methodology for the Redesign of Compressor Blades Undergoing Nonlinear Structural Interactions: Application to Blade-tip/Casing Contacts</title>
            <title xml:lang="fr">Méthodologie pour la reconception d’aubes de compresseurs soumises à des interactions de contact non linéaires : application aux contacts aube/carter</title>
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                <forename type="first">Solène</forename>
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                <title xml:lang="en">Methodology for the Redesign of Compressor Blades Undergoing Nonlinear Structural Interactions: Application to Blade-tip/Casing Contacts</title>
                <title xml:lang="fr">Méthodologie pour la reconception d’aubes de compresseurs soumises à des interactions de contact non linéaires : application aux contacts aube/carter</title>
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                    <forename type="first">Florence</forename>
                    <surname>Nyssen</surname>
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                    <forename type="first">Charles</forename>
                    <surname>Audet</surname>
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                    <forename type="first">Alain</forename>
                    <surname>Batailly</surname>
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                <title level="j">Journal of Engineering for Gas Turbines and Power</title>
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                  <date type="datePub" subtype="inPress">2022</date>
                  <date type="dateEpub">2022-09-22</date>
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                <term xml:lang="en">nonlinear structural interactions</term>
                <term xml:lang="en">blade redesign</term>
                <term xml:lang="en">compressor blades</term>
                <term xml:lang="en">blade-tip/casing contacts</term>
                <term xml:lang="fr">reconception d’aubes</term>
                <term xml:lang="fr">contacts aube/carter</term>
                <term xml:lang="fr">aubes de compresseur</term>
                <term xml:lang="fr">interactions structurales non linéaires</term>
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              <p>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.</p>
            </abstract>
            <abstract xml:lang="fr">
              <p>Ces dix dernières années, la volonté d’améliorer l’efficacité des moteurs d’avions a conduit à repousser les frontières des conditions opératoires bien au-delà d’un contexte structurel linéaire. Les interfaces non linéaires, telles que l’interface de contact aube/carter, sont présentes en conditions opératoires nominales. Pourtant, les méthodologies de conception d’aubes actuelles reposent encore sur des considérations structurales empiriques, souvent linéaires, qui peuvent mener à de coûteuses opérations de reconception. L’objectif de ce travail est de proposer une méthodologie pour la reconception d’aubes de compresseurs soumises à des interactions structurales non linéaires. Un processus de reconception en trois étapes est considéré : (1) la paramétrisation d’une aube existante, (2) la mise à jour de l’aube en fonction d’un critère de performance substitut et (3) la vérification des performances de l’aube optimisée. Une méthode de paramétrisation bi-directionnelle originale est proposée: elle permet à la fois de paramétrer des aubes existantes et de générer des modèles à partir de paramètres d’aubes. Comme preuve de concept, la reconception par rapport aux contacts aubes/carter des aubes de la NASA rotor 37 (compresseur) et rotor 67 (soufflante) est effectuée. Des modèles paramétrés haute-fidélité des aubes initiales sont obtenus et leur réponse dynamique à des interactions de contact est analysée. Les géométries sont mises à jour en fonction de leur consommation de jeu car la minimisation de cette quantité a conduit à des effets bénéfiques sur les interactions de contact considérées. La méthodologie proposée permet de mieux évaluer la pertinence de ce critère de performance dans le contexte des interactions de contact aube/carter.</p>
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