Boundary Layer Ingestion (BLI) is currently being researched as a potential method to improve efficiency and decrease emissions for the next generation of commercial aircraft.  While re-energizing the boundary layer formed over the fuselage of an aircraft has many system level benefits, ingesting the low velocity boundary layer flow through a serpentine inlet into a turbofan engine adversely affects the performance of the engine.  The available literature has only yielded studies of the effects of this specific type of inlet distortion on engine performance in the form of numerical simulations.  This work seeks to provide an experimental analysis of the effects of BLI-type distortion on a turbofan engine's performance.  A modified JT15D-1 turbofan engine was investigated in this study.  Inlet flow distortion was created by a layered wire mesh distortion screen designed to create a total pressure distortion profile at the aerodynamic interface plane (AIP) similar to NASA's Inlet A boundary layer ingesting inlet flow profile.  Results of this investigation showed a 15.5% decrease in stream thrust and a 14% increase in TSFC in the presence of BLI-type distortion. Flow measurements at the AIP and the bypass nozzle exit plane provided information about the losses throughout the fan flow path.  The presence of the distortion screen resulted in a 24% increase in mass-averaged entropy production along the entire fan flow path compared to the non-distorted test.  A mass-averaged fan flow path efficiency was also calculated assuming an isentropic process as ideal.  The non-distorted fan flow path efficiency was computed to be 60%, while the distorted fan flow path efficiency was computed to be 50.5%, a reduction in efficiency of 9.5%.  The entropy generation between ambient conditions and the AIP was compared to the entropy production along the entire fan flow path.  It was found that the majority of entropy generation occurred between the AIP and bypass nozzle exit.  Based on flow measurements at the bypass nozzle exit plane, it was concluded that inlet flow distortion should be located away from the tip region of the fan in order to minimize losses in a very lossy region.  It was also determined that the fan and bypass duct process the different regions of the total pressure distortion in different ways.  In some regions the entropy production decreased for the distorted test compared to the clean test, while in other regions the entropy production increased for the distorted test compared to the clean test.  Finally, it was found that small improvements in total pressure and total temperature variation at the bypass nozzle exit plane will greatly improve the fan flow path efficiency and entropy generation, thereby decreasing performance losses. / Master of Science

The combination of traditional passive acoustic liners with Herschel-Quincke (HQ) waveguides is proposed in this work as a device for Turbofan Engine Noise Control. The approach consists of installing circumferential arrays of HQ tubes on the lined sector of the inlet of a turbofan engine. A theoretical model is developed to predict the performance of this system assuming that the engine inlet is a circular lined duct with uniform mean flow. The tube-duct interfaces are modeled as finite piston sources that couple the sound field inside the duct with the dynamics of the HQ tubes. The finite piston source radiation is modeled in terms of a new closed form Green's function, which is found as the solution of the non-homogeneous convected acoustic wave equation with soft wall boundary conditions. The Green's function is extended from a point source to a finite piston by using the Divergence Theorem in the appropriate form. The dynamics of the HQ tube are both modeled as plane waves inside a straight tube and experimentally determined. The experimental determination of the HQ-dynamics is undertaken using impedance tubes with a 4-microphone technique. The newly developed theoretical model was used to predict the performance of a combined HQ-Liner system, which was tested on a scale simulated turbofan rig. The model is validated for broadband noise with the experimental data obtained from this test rig. The analytical predictions are shown to correlate well with experimental data. The results of the application of a HQ-Liner on a turbofan engine show a great potential in order to improve the performance of traditional passive acoustic liners. / Ph. D.

Résumé: Cette dissertation s’intéresse aux méthodes numériques dans le domaine de l’acoustique. Les propriétés acoustiques d’un produit sont devenues une part intégrante de la conception. En effet, de nos jours le bruit est perçu comme une nuisance par le consommateur et constitue un critère de vente. Il y a de plus des normes à respecter. Les méthodes numériques permettent de prédire la propagation sonore et constitue dès lors un outil de conception incontournable pour réduire le temps et les coûts de développement d’un produit. Cette dissertation considère la propagation d’ondes acoustiques dans le domaine fréquentiel en tenant compte de la présence d’un écoulement. Nous pouvons citer comme application industrielle, le rayonnement d’une nacelle de réacteur d’avion. Le but de la thèse est de proposer une nouvelle méthode et démontrer ses performances par rapport aux méthodes actuellement utilisées (i.e. la méthode des éléments finis). L’originalité du travail consiste à étendre la méthode de partition de l’unité polynomiale dans le cadre de la propagation acoustique convectée, pour des domaines extérieurs. La simulation acoustique dans des domaines de dimensions infinies est réalisée dans ce travail à l’aide d’un couplage entre éléments finis et éléments infinis. La dissertation présente la formulation de la méthode pour des applications axisymétriques et tridimensionnelles et vérifie la méthode en comparant les résultats numériques obtenus avec des solutions analytiques pour des applications académiques (i.e. propagation dans un conduit, rayonnement d’un multipole, bruit émis par la vibration d’un piston rigide, etc.). Les performances de la méthode sont ensuite analysées. Des courbes de convergences illustrent à une fréquence donnée, la précision de la méthode en fonction du nombre d’inconnues. Tandis que des courbes de performances présentent le temps de calcul nécessaire pour obtenir une solution d’une précision donnée en fonction de la fréquence d’excitation. Ces études de performances montrent l’intérêt de la méthode présentée. Le rayonnement d’un réacteur d’avion a été abordé dans le but de vérifier la méthode sur une application de type industriel. Les résultats illustrent la propagation pour une nacelle axisymétrique en tenant compte de l’écoulement et la présence de matériau absorbant dans la nacelle et compare les résultats obtenus avec la méthode proposée et ceux obtenus avec la méthode des éléments finis. Les performances de la méthode de la partition de l’unité dans le cadre de la propagation convectée en domaines infinis sont présentées pour des applications académiques et de type industriel. Le travail effectué illustre l’intérêt d’utiliser des fonctions polynomiales d’ordre élevé ainsi que les avantages à enrichir l’approximation localement afin d’améliorer la solution sans devoir créer un maillage plus fin. Summary: Environmental considerations are important in the design of many engineering systems and components. In particular, the environmental impact of noise is important over a very broad range of engineering applications and is increasingly perceived and regulated as an issue of occupational safety or health, or more simply as a public nuisance. The acoustic quality is then considered as a criterion in the product design process. Numerical prediction techniques allow to simulate vibro-acoustic responses. The use of such techniques reduces the development time and cost. This dissertation focuses on acoustic convected radiation in outer domains such as it is the case for turbofan radiation. In the current thesis the mapped infinite partition of unity method is implemented within a coupled finite and infinite element model. This method allows to enrich the approximation with polynomial functions. We present axisymmetric and three-dimensional formulations, verify and analyse the performance of the method. The verification compares computed results with the proposed method and analytical solutions for academic applications (i.e. duct propagation, multipole radiation, noise radiated by a vibrating rigid piston, etc.) . Performance analyses are performed with convergence curves plotting, for a given frequency, the accuracy of the computed solution with respect to the number of degrees of freedom or with performance curves, plotting the CPU time required to solve the application within a given accuracy, with respect to the excitation frequency. These performance analyses illustrate the interest of the mapped infinite partition of unity method. We compute the radiation of an axisymmetric turbofan (convected radiation and acoustic treatments). The aim is to verify the method on an industrial application. We illustrate the radiation and compare the mapped infinite partition of unity results with finite element computations. The dissertation presents the mapped partition of unity method as a computationally efficient method and illustrates its performances for academic as well as industrial applications. We suggest to use the method with high order polynomials and take the advantage of the method which allows to locally enrich the approximation. This last point improves the accuracy of the solution and prevent from creating a finer mesh.

The demand for turbofan engine performance development is high in the military industry. However, to develop the engine, it is necessary to predict its performance, and engine testing is both time-consuming and costly. Therefore, simulation is an effective approach to predicting the engine’s performance. During this thesis, a low bypass ratio turbofan engine is created in the simulation tool Simulink to investigate the engine performance throughout different flight conditions and maneuvers. The engine model is constructed for the future fighter aircraft at SAAB Aeronautics. The development of a design point has received particular attention throughout the work. After that, the development of proven methods for estimating engine performance of other parts of the flight envelope, resulting in increased model fidelity and enabling simulations of the same engine type but under different conditions and flight cases. To summarize, the tests of the engine model are successful under various design characteristics, conditions, and flight cases. In addition, simulations of the performance evaluation of fighter aircraft engines have been accomplished.

No description available.

In this dissertation the influence of vane sweep on rotor-stator interaction noise is investigated. In an analytical approach, the interaction of a convected gust, representing the rotor viscous wake, with a cascade of finite span swept airfoils, representing the stator, is analyzed. The analysis is based on the solution of the exact linearized equations of motion. High-frequency convected gusts for which noise generation is concentrated near the leading edge of the airfoils are considered. In a preliminary study, the problem of an isolated finite span swept airfoil interacting with a convected gust is analyzed. Using Fourier transform methods and the Wiener-Hopf technique, an approximate solution for this problem is developed. Closed form expressions for the acoustic farfield are obtained and used in a parametric study to assess the effect of airfoil sweep on noise generation. Results indicate that sweep can substantially reduce the farfield noise levels for a single airfoil. Utilizing the single airfoil model, an approximate solution to the problem of noise radiation from a cascade of finite span swept airfoils interacting with a convected gust is derived. Only upstream radiated noise is considered. Neglecting the weak coupling between the adjacent leading edges at high frequencies, the cascade solution is constructed as a superposition of acoustic farfields emanating from an infinite number of isolated airfoils. A parametric study of noise generated by gust-cascade interaction is then carried out to assess the effectiveness of vane sweep in reducing rotor-stator interaction noise. The results of the parametric study show that, over a fairly wide range of conditions, sweep is beneficial in reducing noise levels. One conclusion of particular importance is that rotor wake twist or circumferential lean substantially influences the effectiveness of vane sweep. The orientation of the vane sweep must be chosen to enhance the natural phase lag caused by wake lean, in which case rather small sweep angles substantially reduce the noise levels.

This Master Thesis was performed within Research & Technology at GKN Aerospace, Trollhättan. GKN Aerospace is participating in the Clean Sky 2 program, delivering the ICC to the UltraFan demonstrator. On this demonstrator, the split and load paths of three components in the compressor module are similar to earlier engine configurations, but GKN wanted to investigate if there are other, more efficient ways of building this structure. The aim of this thesis was therefore to investigate if there is a more efficient architecture and design of the static components in the compressor module for the UltraFan engine. Utilizing a more efficient architecture and design GKN can, in exchange of undertaking a larger part of the engine, provide engine manufacturers a more lightweight solution. This goes accordingly with GKN’s aim to undertake a larger total share of aero engines. The approach for concept development during this thesis has been based on a five-step concept generation method. First knowledge about different engine architectures and component designs was gathered through qualitative interviews with experts. This was followed by the creating of a simplified baseline, or reference, model based on the UltraFan compressor module. A Finite Element Analysis, FEA, of the baseline was performed which generated further understanding about the current design. The knowledge gathered, both in the interviews and by evaluating the baseline, was used as a basis when generating concepts. Four concepts were evaluated using a screening matrix, where the concept that best satisfied the set requirements was further developed. The refined concept was then compared to the baseline, by analyzing stiffness and ovalization for both designs. The results from the concept evaluation indicated that possible weight savings can be made, but further investigation and refinements are required to ensure fulfillment of the set stiffness and deformation requirements. A further refined version of the baseline simulation model and associated methods could be used to evaluate how different designs affect the performance in terms of weight, stiffness and ovalization.

Et une quantification de la distorsion due à l’effet potentiel des OGVs et de celle due à l’asymétrie de l’entrée d’air sont proposées. Les effets de la distorsion sur l’aérodynamique sont mis en évidence avec notamment une modification importante des sillages des pales de la soufflante, des chocs et de la charge instationnaire exercée sur les différentes pales et aubes. Des prévisions Les objectifs en termes de réduction de la consommation et du bruit émis par les moteurs d’avions ont progressivement mené aux architectures à très grand taux de dilution (UHBR). Leur géométrie est caractérisée par une entrée d’air courte et par une réduction de l’espace entre la soufflante et les aubes du redresseur du flux secondaire (OGVs), entraînant alors une augmentation de l’inhomogénéité azimutale de l’écoulement au niveau de la soufflante. Cette inhomogénéité, appelée distorsion, pourrait impacter le bruit tonal généré par le module de la soufflante. Ce bruit est généralement supposé être dominé par le mécanisme d’interaction des sillages des pales de la soufflante avec les OGVs. En régime transsonique, le bruit de choc et le bruit de charge stationnaire deviennent également prépondérants. L’augmentation de la distorsion pourrait être à l’origine de nouvelles sources de bruit en interagissant avec les pales de la soufflante et l’objectif de cette thèse est d’évaluer leur contribution. Les effets de la distorsion sur les mécanismes de bruit déjà existants sont également analysés. Cette étude est réalisée à l’aide de simulations numériques des équations instationnaires de Navier-Stokes moyennées (URANS). Un module complet de fan est considéré sur 360 degrés et se compose d’un conduit d’entrée d’air, de la soufflante et des redresseurs des flux primaire et secondaire (IGVs/OGVs). Le redresseur du flux secondaire est typique des moteurs actuels avec un pylône intégré et deux entrées d’air différentes sont étudiées de manière à isoler les effets de la distorsion d’entrée d’air. La première est axisymétrique et ne produit donc pas de distorsion alors que la deuxième ne l’est pas et produit un niveau de distorsion typique de ceux attendus dans les moteurs UHBR. Une description acoustiques basées sur les approches directe et hybride sont réalisées et soulignent la contribution importante des sources localisées sur les pales de la soufflante sur le bruit amont. Le bruit aval reste dominé par les sources sur les OGVs mais est tout de même impacté par la distorsion d’entrée d’air via la modification des sillages. / Fuel consumption and noise reduction trigger the evolution of aircraft engines towards Ultra High Bypass Ratio (UHBR) architectures. Their short air inlet design and the reduction of their interstage length lead to an increased circumferential inhomogeneity of the flow close to the fan. This inhomogeneity, called distortion, may have an impact on the tonal noise radiated from the fan module. Usually, such a noise source is supposed to be dominated by the interaction of fan-blade wakes with Outlet Guide Vanes (OGVs). At transonic tip speeds, the noise generated by the shocks and the steady loading on the blades also appears to be significant. The increased distortion may be responsible for new acoustic sources while interacting with the fan blades and the present work aims at evaluating their contribution. The effects of distortion on the other noise mechanisms are also investigated. The work is based on full-annulus simulations of the Unsteady Reynolds-Averaged Navier-Stokes (URANS) equations. A whole fan module including the inlet duct, the fan and the Inlet and Outlet Guide Vanes (IGVs/OGVs) is studied. The OGV row is typical of current engine architecture with an integrated pylon and two different air inlet ducts are compared in order to isolate the effects of inlet distortion. The first one is axisymmetric and does not produce any distortion while the other one is asymmetric and produces a level of distortion typical of the ones expected in UHBR engines. A description and a quantification of the distortion that is caused by both the potential effect of the OGVs and the inlet asymmetry are proposed. The effects of the distortion on aerodynamics are highlighted with significant modifications of the fanblade wakes, the shocks and the unsteady loading on the blades and on the vanes. Both direct and hybrid acoustic predictions are provided and highlight the contribution of the fan-blade sources to the upstream noise. The downstream noise is still dominated by the OGV sources but it is shown to be significantly impacted by the inlet distortion via the modification of the impinging wakes.

A computional model is developed for prediction of noise emission from na existing or new turbofan engine. This model allows the simulation of noise generation from high bypass ratio turbofan engines, appropriate for use with computational programs for gas turbine performance developed at ITA. Analytical and empirical methods are used for spectrum shape, spectrum level, overall noise and free-field directivity noise. The most significant noise sources in turbofan engines are modeled: fan, compressor, combustion chamber, turbine, jet (separate streams or mixed jet), with corrections for forward speed, atmospheric attenuation, ground reflection, and nacelle acoustic treatment (perforate liners). The procedures for component noise prediction are combined to yield total turbofan engine noise emission, as a funtion of engine operation condition and of observer (distance and directivity angle).

O presente trabalho tem a finalidade de descrever a metodologia de desenvolvimento e acompanhamento utilizado no projeto de um sistema de proteção, detecção e extinção de fogo em um motor turbofan de alta razão de passagem. A metodologia de desenvolvimento consiste no detalhamento dos passos preliminares, levantamento dos requisitos de certificação aplicáveis ao sistema, entradas de projeto, ensaios para a certificação, documentos a serem gerados e métodos de acompanhamento. Como resultado, é apresentada a descrição de um sistema real de proteção, detecção e extinção de fogo gerado a partir da metodologia proposta, além de realçar os pontos fundamentais da metodologia de desenvolvimento apresentada.