Este trabalho se propõe a simular a emissão de NOx na condição de decolagem, para motores de diversos fabricantes, usando o software de simulação de desempenho GasTurb (versão 10) e obter resultados próximos aos dados experimentais apresentados na planilha de certificação de emissões da ICAO (Organização Internacional de Aviação Civil). O GasTurb é utilizado sobretudo em cálculos do ponto de projeto e permite similar, numa única subrotina, vários motores. Mais que isso, objetiva-se apresentar os passos a serem seguidos para a avaliação dos ciclos completes de emissões (LTO), usando-se o GasTurb, embora não seja o objetivo dessa dissertação um estudo detalhado desses ciclos. Finalmente, mostra-se que um modelo empírico de emissões de NOx que depende apenas da pressão e temperatura de entrada na câmara de combustão (P3 e T3) prevê com boa confiabilidade as emissões experimentais desse poluente em combustores convencionais.

In this study, acoustic noise radiation through a duct in frequency domain is analyzed. Frequency domain linearized Euler equations are solved for turbofan exhaust noise propagation and radiation. The geometry in studied cases is assumed as axisymmetric. The acoustic waves are decomposed into periodic azimuthal modes. Characteristic boundary conditions, and buffer zone boundary conditions are employed. Iterative type pseudo time integration is employed. Nonuniform background flow effect on the radiation pattern is experienced. All computations are performed in parallel using MPI library routines in computer cluster. Results proved that the one with the buffer zone has a better radiation characteristic than the characteristic one because of absorbtion of spurious waves. It is seen that the efficiency of the buffer zone is frequency dependent.

L'objectif de ce travail est de proposer une nouvelle démarche pour améliorer et accélérer les études de dimensionnement des pièces de turboréacteurs en avant-projets. Il s'agit de fournir une méthodologie complète pour la conception robuste sous contraintes. Cette méthodologie consiste en trois étapes : la réduction de la dimension et la méta-modélisation, la conception robuste sous contraintes puis la résolution de problèmes inverses sous contraintes. Ce sont les trois principaux sujets abordés dans cette thèse. La réduction de la dimension est un pré-traitement indispensable à toute étude. Son but est de ne conserver, pour une sortie choisie du système, que les entrées influentes. Ceci permet de réduire la taille du domaine d'étude afin de faciliter la compréhension du système et diminuer les temps de calculs des études. Les méthodes de méta-modélisations contribuent également à ces deux objectifs. L'idée est de remplacer le code de calculs coûteux par un modèle rapide à évaluer et qui représente bien la relation entre la sortie étudiée et les entrées du système. La conception robuste sous contraintes est une optimisation bi-objectifs où les différentes sources d'incertitudes du système sont prises en compte. Il s'agit, dans un premier temps, de recenser et modéliser les incertitudes puis de choisir une méthode de propagation de ces incertitudes dans le code de calculs. Ceci permet d'estimer les moments (moyenne et écart-type) de la loi de la sortie d'intérêt. L'optimisation de ces moments constitue les deux objectifs de la conception robuste. En dernier lieu, il s'agit de choisir la méthode d'optimisation multi-objectifs qui sera utilisée pour obtenir l'optimum robuste sous contraintes. La partie innovante de cette thèse porte sur le développement de méthodes pour la résolution de problèmes inverses mal posés. Ce sont des problèmes pour lesquels il peut y avoir une infinité de solutions constituant des ensembles non convexes et même disjoints. L'inversion a été considérée ici comme un complément à l'optimisation robuste dans laquelle l'optimum obtenu ne satisfaisait pas une des contraintes. Les méthodes d'inversion permettent alors de résoudre ce problème en trouvant plusieurs combinaisons des entrées qui satisfont la contrainte sous la condition de rester proche de l'optimum robuste. Le but est d'atteindre une valeur cible de la contrainte non satisfaite tout en respectant les autres contraintes du système auxquelles on ajoute la condition de proximité à l'optimum. Appliquée au dimensionnement d'un compresseur HP en avants-projets, cette méthodologie s'inscrit dans l'amélioration et l'accélération des études marquées par de nombreux rebouclages chronophages en termes de ressources informatiques et humaines. / The aim of this PhD dissertation is to propose a new approach to improve and accelerate preliminary design studies for turbofan engine components. This approach consists in a comprehensive methodology for robust design under constraints, following three stages : dimension reduction and metamodeling, robust design under constraints and finally inverse problem solving under constraints. These are the three main subjects of this PhD dissertation. Dimension reduction is an essential pre-processing for any study. Its aim is to keep only inputs with large effects on a selected output. This selection reduces the size of the domain on which is performed the study which reduces its computational cost and eases the (qualitative) understanding of the system of interest. Metamodeling also contributes to these two objectives by replacing the time-consuming computer code by a faster metamodel which approximates adequately the relationship between system inputs and the studied output. Robust design under constraints is a bi-objectives optimization where different uncertainty sources are included. First, uncertainties must be collected and modeled. Then a propagation method of uncertainties in the computation code must be chosen in order to estimate moments (mean and standard deviation) of output distribution. Optimization of these moments are the two robust design objectives. Finally, a multi-objectives optimization method has to be chosen to find a robust optimum under constraints. The development of methods to solve ill-posed inverse problems is the innovative part of this PhD dissertation. These problems can have infinitely many solutions constituting non convex or even disjoint sets. Inversion is considered here as a complement to robust design in the case where the obtained optimum doesn't satisfy one of the constraints. Inverse methods then enable to solve this problem by finding several input datasets which satisfy all the constraints and a condition of proximity to the optimum. The aim is to reach a target value of the unsatisfied constraint while respecting other system constraints and the optimum proximity condition. Applied to preliminary design of high pressure compressor, this methodology contributes to the improvement and acceleration of studies currently characterized by a numerous of loopbacks which are expensive in terms of cpu-time and human resources.

Master’s thesis deals with the issue of a conversion of a twin-engined piston aircraft Beechcraft B60 Duke into turboprop engines Walter M601 or Pratt & Whitney Canada PT6.The paper focuses on a financial analysis of conducting of the conversion, resources needed for a certification, authorization for the traffic in the Czech Republic and determination of the rate of return on investment.The thesis further deals with elaborating of the flight and prerformance characteristics, operation costs of both of the proposed engines and compares them with current characteristics and operation costs.

No description available.

L’évolution des turboréacteurs vers des taux de dilution toujours plus importants est associée à de nouvelles problématiques. Parmi elles, le raccourcissement de l’entrée d’air et de la tuyère est associé à une diminution du gain apporté par les traitements acoustiques de nacelle. La contribution des traitements situés dans l’espace entre la soufflante et le stator redresseur (OGV) va donc prendre de l’importance par rapport à l’ensemble des traitements. Cette zone, également appelée “interstage”, est caractérisée par une forte giration de l’écoulement moyen due à l’entraînement du fluide par le rotor. L’objectif de ce travail est de développer un modèle analytique afin d’évaluer l’effet de la giration sur le comportement des traitements acoustiques dans l’interstage, ainsi que sur le bruit à large-bande rayonnant en amont dû à l’interaction de la turbulence en aval de la soufflante avec les aubes des stators (OGV). Dans un premier temps, l’évolution de petites perturbations dans écoulement moyen tournant et cisaillé dans un conduit rigide est étudiée. Après avoir introduit les équations ainsi que les hypothèses du problème, l’analogie acoustique de Posson & Peake [122] est présentée. L’effet de la giration sur le contenu modal dans un conduit rigide est mis en évidence pour plusieurs types d’écoulements tournants. En particulier, le décalage des fréquences de coupures est étudié. L’étude est ensuite étendue au cas d’un conduit annulaire traité acoustiquement. Une attention particulière est portée sur la condition aux limites à appliquer aux parois du conduit. Dans ce cadre, une correction due aux effets centrifuges est apportée à la condition aux limites de Myers [101]. Une extension du modèle de Brambley [24] est aussi proposée afin de prendre en compte l’effet de l’épaisseur de la couche limite aux parois du conduit dans le cas tournant. Les effets combinés de la rotation et de la condition aux limites sur le contenu modal sont ensuite étudiés. En outre, une relation de dispersion pour les modes de surfaces en présence d’écoulement tournant est développée. À partir des développements précédents, un modèle de transmission acoustique est proposé afin d’évaluer l’effet de la giration sur le comportement des traitements acoustiques. La méthode repose sur le principe de raccordement modal appliqué à la conservation du débit massique et de l’enthalpie totale aux interfaces séparant les sections rigides et traitées. Une nouvelle méthode de projection basée sur les propriétés des polynômes de Chebyshev est proposée. À partir de ce modèle, l’efficacité des traitements acoustiques est étudiée pour différents écoulements tournants. Enfin, un modèle de prédiction du bruit à large-bande d’interaction rotor-stator est établi à partir de l’analogie de Posson & Peake [122], dans le but de prendre en compte l’effet de la giration sur la puissance acoustique rayonnée en amont. Le terme source est calculé selon le formalisme de Posson et al. [120]. Le modèle ainsi développé permet de prendre en compte une évolution radiale des paramètres géométriques et des propriétés statistiques de la turbulence incidente. Le modèle est ensuite évalué sur le cas test NASA SDT pour différents régimes et géométries. / The advent of modern turbofan engines such as UHBR goes along with new issues. Amongst others, the shortening of the inlet and exhaust yield a relatively higher importance of the liners located inside the interstage, where the flow is highly swirling. The present work aims at developing analytical models to assess the effect of the swirl both on the behavior of the interstage liners and on the upstream radiation of the fan-OGV interaction broadband boise. The evolution of small fluctuations in a rigid annular duct containing a swirling and sheared mean flow are studied first. After having introduced the governing equations and the main assumptions, the acoustic analogy of Posson & Peake [122] tailored to an annular duct with swirl and shear is presented. The effect of the swirl on the modal content in a rigid annular duct is highlighted for different types of swirl. In particular the shift of the cut-on thresholds is studied. Then, the modal analysis is extended to a duct with lined walls. A particular attention is paid on the boundary condition. Notably, a correction of the classical Myers boundary condition [101] is proposed to account for the centrifugal effects. An extension of Brambley’s boundary condition [24] is also derived to account for the boundary layer thickness to first order. The effect of both the swirl and the boundary condition on the modal content are studied. Besides, a dispersion relation for the surface waves is derived for the corrected Myers boundary condition. Based on the previous modal analyses, a transmission tool is developed to assess the effect of the swirl on the efficiency of a liner. The method, which relies on the mode-matching approach, is based on the conservation of the total enthalpy and the mass flow at the interfaces between the rigid and the lined sections. Due to the nature of the eigenfunctions, a new projection method based on the Chebyshev polynomial properties is proposed. Thanks to this model, the absorption is assessed for different types of swirl. Finally, a rotor-stator interaction broadband noise prediction model is derived from Posson & Peake’s acoustic analogy [122], to account for the effect of the swirl on the upstream radiated acoustic power. The source term is computed according to Posson et al.’s model [120]. It allows considering a radial variation of the geometry and the statistical properties of the incident turbulence. The model is assessed on the NASA SDT test case and the effect of the swirl is evaluated for several stator geometries and regimes.

Sverige har idag några av Europas äldsta militära transportflygplan av typen TP 84 Lockheed Martin C-130H Hercules. Försvarsmakten har beslutat om att modifiera flygplanen så att de kan fortsätta att flyga fram till 2030 men på sikt måste ett nytt system köpas in. Uppsatsen avhandlar det beprövade flygplanet Lockheed Martin C-130J mot det nya Embraer KC-390. Analysen avhandlar en komparativ jämförelse mellan två olika transportflygplan samt systemens införande i Försvarsmakten. Fallet är en del av en jämförelse mellan flygplanen med turboprop-och turbofläktmotorer. Jämförelsen kommer att kopplas mot Andersson et al:s teori om militär nytta. Slutsatserna från analysen är att vid ett införande av C-130J kommer ett driftsäkert system med lång erfarenhet av att operera i konfliktzoner med provisoriska landningsbanor tillföras Försvarsmakten. Flygplanets prestanda och begränsningar är redan kända. Vid införandet av KC- 390 är uppgifterna om prestanda och begränsningar en osäkerhet då systemet ännu inte är i tjänst. Osäkerheter som förmågan att operera från provisoriska flygfält måste tas i beaktande. Dock är flygplanet bättre avseende räckvidd, lastkapacitet samt hastighet, detta på grund av flygplanets turbofläktmotorer. / This thesis considers the problem of Sweden currently having some of Europe's oldest military Hercules transport aircraft of the type TP 84 Lockheed Martin C-130H Hercules. The Swedish Armed Forces have decided to modify the aircraft to extend it to 2030, but in the long term a new system must be procured. This thesis deals with the proven aircraft Lockheed Martin C-130J compared to the new Embraer KC-390. The approach uses Andersson et al's theory of military utility to compare two different transport aircraft as well as the system's introduction into the Swedish Armed Forces. The case is part of a comparison of aircraft with turboprop against turbofan engines. The conclusions from the analysis are that the C-130J is an operational system with long experience of operating in conflict zones from provisional runways, and the aircraft's performance and limitations are already known. With the KC-390, performance and limit data are an uncertainty whilst the system is not yet in service; as is its ability to operate from temporary airports. However, this aircraft is better in terms of range, load capacity and speed, due to the aircraft's turbofan engines.

Zapfluft und Wellenleistung wird den Triebwerken entnommen, um die Energie für beispielsweise die Kraftstoffpumpen, das Inflight Entertainment oder die Flügelvorderkantenenteisung zu erzeugen. Diese Energiegenerierung, hat einen Anstieg des Kraftstoffverbrauches zur Folge. Es hat sich herausgestellt, dass die Stelle der Zapfluftentnahme einen starken Einfluss auf den Gradienten des Brennstoffverbrauches hat. Das Projekt beschäftigt sich mit zwei- und dreiwelligen Turbofantriebwerken und untersucht an ihnen, die Effekte der Leistungsnahmen. Als Simulationssoftware wurde GasTurb 8.0 eingesetzt und auf die integrierten Triebwerkskonfigurationen zurückgegriffen. Ziel der Arbeit ist die Ermittlung einer mathematischen Beziehung zur Berechnung des zusätzlichen Kraftstoffmassenstromes infolge einer Zapfluft- oder Wellenleistungsentnahme. So stellt sich die Frage, welche Triebwerksparameter dafür berücksichtigt werden müssen. Eine Wellenleistungsentnahme verursacht beispielsweise einen linearen Anstieg des spezifischen Kraftstoffverbrauches. Ist diese Zunahme, identisch mit der einer Zapfluftentnahme? Am Ende der Kapitel werden die Ergebnisse mit Literaturwerten verglichen und versucht Tendenzen zu erkennen bzw. bestehende zu erhärten.

Purpose of this project is a) the evaluation of the Thrust Specific Fuel Consumption (TSFC) of jet engines in cruise as a function of flight altitude, speed and thrust and b) the determination of the optimum cruise speed for maximum range of jet airplanes based on TSFC characteristics from a). Related to a) a literature review shows different models for the influence of altitude and speed on TSFC. A simple model describing the influence of thrust on TSFC seems not to exist in the literature. Here, openly available data was collected and evaluated. TSFC versus thrust is described by the so-called bucket curve with lowest TSFC at the bucket point at a certain thrust setting. A new simple equation was devised approximating the influence of thrust on TSFC. It was found that the influence of thrust as well as of altitude on TSFC is small and can be neglected in cruise conditions in many cases. However, TSFC is roughly a linear function of speed. This follows already from first principles. Related to b) it was found that the academically taught optimum flight speed (1.316 times minimum drag speed) for maximum range of jet airplanes is inaccurate, because the derivation is based on the unrealistic assumption of TSFC being constant with speed. Taking account of the influence of speed on TSFC and on drag, the optimum flight speed is only about 1.05 to 1.11 the minimum drag speed depending on aircraft weight. The amount of actual engine data was extremely limited in this project and the results will, therefore, only be as accurate as the input data. Results may only have a limited universal validity, because only four jet engine types were analyzed. One of the project's original value is the new simple polynomial function to estimate variations in TSFC from variations in thrust while maintaining constant speed and altitude.

Purpose - This thesis presents a comparison of aircraft design concepts to identify the superior propulsion system model among turbo-hydraulic, turbo-electric and classic jet propulsion with respect to Direct Operating Costs (DOC), environmental impact and fuel burn. --- Approach - A simple aircraft model was designed based on the Top-Level Aircraft Requirements of the Airbus A320 passenger aircraft, and novel engine concepts were integrated to establish new models. Numerous types of propulsion system configurations were created by varying the type of gas turbine engine and number of propulsors. --- Findings - After an elaborate comparison of the aforementioned concepts, the all turbo-hydraulic propulsion system is found to be superior to the all turbo-electric propulsion system. A new propulsion system concept was developed by combining the thrust of a turbofan engine and utilizing the power produced by the turbo-hydraulic propulsion system that is delivered via propellers. The new partial turbo-hydraulic propulsion concept in which 20% of the total cruise power is coming from the (hydraulic driven) propellers is even more efficient than an all turbo-hydraulic concept in terms of DOC, environmental impact and fuel burn. --- Research Limitations - The aircraft were modelled with a spreadsheet based on handbook methods and relevant statistics. The investigation was done only for one type of reference aircraft and one route. A detailed analysis with a greater number of reference aircraft and types of routes could lead to other results. --- Practical Implications - With the provided spreadsheet, the DOC and environmental impact can be approximated for any commercial reference aircraft combined with the aforementioned propulsion system concepts. --- Social Implications - Based on the results of this thesis, the public will be able to discuss the demerits of otherwise highly lauded electric propulsion concepts. --- Value - To evaluate the viability of the hydraulic propulsion systems for passenger aircraft using simple mass models and aircraft design concept.