Relevant bibliographies by topics / Aeronautical engine

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Aeronautical engine'

Author: Grafiati
Published: 4 June 2021
Last updated: 1 February 2022

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the lists of relevant articles, books, theses, conference reports, and other scholarly sources on the topic 'Aeronautical engine.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Journal articles on the topic "Aeronautical engine"

1

Lemco, Ian. "Wittgenstein's aeronautical investigation." Notes and Records of the Royal Society 61, no. 1 (December 22, 2006): 39–51. http://dx.doi.org/10.1098/rsnr.2006.0163.

Full text
Abstract:
After a rigorous German education in the physical sciences, young Ludwig Wittgenstein entered Manchester University as an aeronautical engineering research student. There he devised and patented a novel aero-engine employing an airscrew propeller driven by blade tip-jets. Within the context of the growth of English aviation during the first half of the twentieth century (including the contributions of many Fellows of the Royal Society) and taking into account related aspects of his life, this paper examines an unfulfilled engineering aspiration. In enlarging upon what Wittgenstein might have accomplished during his stay at Manchester, it contrasts his invention with later comparable proven designs, albeit applied to hybrid rotorcraft. His engine employed centrifugal flow compression and arguably was a precursor of Sir Frank Whittle's gas turbine. In conclusion, reasons are given for Wittgenstein's departure from Manchester.
APA, Harvard, Vancouver, ISO, and other styles
2

Faruoli, Maria, Annarita Viggiano, Paolo Caso, and Vinicio Magi. "A Numerical Analysis of the Air-Cooling System of a Spark Ignition Aeronautical Engine." E3S Web of Conferences 197 (2020): 06003. http://dx.doi.org/10.1051/e3sconf/202019706003.

Full text
Abstract:
It is well known that spark ignition internal combustion engines for aeronautical applications operate within a specific temperature range to avoid structural damages, detonations and loss of efficiency of the combustion process. An accurate assessment of the cooling system performance is a crucial aspect in order to guarantee broad operating conditions of the engine. In this framework, the use of a Conjugate Heat Transfer method is a proper choice, since it allows to estimate both the heat fluxes between the engine walls and the cooling air and the temperature distribution along the outer wall surfaces of the engine, and to perform parametric analyses by varying the engine operating conditions. In this work, the air-cooling system of a 4-cylinder spark ignition engine, designed by CMD Engine Company for aeronautical applications, is analysed in order to evaluate the amount of the air mass flow rate to guarantee the heat transfer under full load operating conditions. A preliminary validation of the model is performed by comparing the results with available experimental data. A parametric study is also performed to assess the influence of the controlling parameters on the cooling system efficiency. This study is carried out by varying the inlet air mass flow rate from 1.0 kg/s to 1.5 kg/s and the temperature of the inner wall surfaces of the engine combustion chambers from 390 K to 430 K.
APA, Harvard, Vancouver, ISO, and other styles
3

Férand, Mélissa, Thomas Livebardon, Stéphane Moreau, and Marlène Sanjosé. "Numerical Prediction of Far-Field Combustion Noise from Aeronautical Engines." Acoustics 1, no. 1 (February 19, 2019): 174–98. http://dx.doi.org/10.3390/acoustics1010012.

Full text
Abstract:
A hybrid methodology combining a detailed Large Eddy Simulation of a combustion chamber sector, an analytical propagation model of the extracted acoustic and entropy waves at the combustor exit through the turbine stages, and a far-field acoustic propagation through a variable exhaust temperature field was shown to predict far-field combustion noise from helicopter and aircraft propulsion systems accurately for the first time. For the single-stream turboshaft engine, the validation was achieved from engine core to the turbine exit. Propagation to the far field was then performed through a modeled axisymmetric jet. Its temperature modified the acoustic propagation of combustion noise significantly and a simple analytical model based on the Snell–Descarte law was shown to predict the directivity for axisymmetric single jet exhaust accurately. Good agreement with measured far-field spectra for all turboshaft-engine regimes below 2 kHz stresses that combustion noise is most likely the dominant noise source at low frequencies in such engines. For the more complex dual-stream turbofan engine, two regime computations showed that direct noise is mostly generated by the unsteady flame dynamics and the indirect combustion noise by the temperature stratification induced by the dilution holes in the combustion chamber, as found previously in the turboshaft case. However, in the turboengine, direct noise was found dominant at the combustor exit for the low power case and equivalent contributions of both combustion noise sources for the high power case. The propagation to the far-field was achieved through the temperature field provided by a Reynolds-Averaged Navier–Stokes simulation. Good agreement with measured spectra was also found at low frequencies for the low power turboengine case. At high power, however, turboengine jet noise overcomes combustion noise at low frequencies.
APA, Harvard, Vancouver, ISO, and other styles
4

McCord, Charles G. "THE AERONAUTICAL ENGINE LABORATORY, NAVAL AIRCRAFT FACTORY, PHILADELPHIA, PENNA." Journal of the American Society for Naval Engineers 37, no. 2 (March 18, 2009): 275–305. http://dx.doi.org/10.1111/j.1559-3584.1925.tb02517.x.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

Fedele, Lorenzo, Luca Di Vito, and Fulvio Enzo Ramundo. "Increasing Efficiency in an Aeronautical Engine through Maintenance Evaluation and Upgrades: Analysis of the Reliability and Performance Improvements under Financial Issues." Energies 13, no. 12 (June 12, 2020): 3059. http://dx.doi.org/10.3390/en13123059.

Full text
Abstract:
This paper defines a methodology for the evaluation of the technical and economic performance of aeronautical engines through the upgrades introduced during its life. The CFM56 is a high-bypass turbofan engine. The variants share a common design, but the details are different. The fan and booster evolved over the different iterations of the engine, as did the compressor, combustor, and turbine sections. Maintenance consists of the activities carried out during the life cycle of an engine to ensure safe, reliable, and economic operation. Maintenance costs represent 20–25% of an airline’s operating costs, of which 35–40% refer to the engine. The changes in the performance parameters indicate the state of the engine in the medium to long term: for example, it is possible to detect blade fouling or data on vibrations, and highlight changes in the characteristic behavior of an engine. This work investigates the behavior of the performance parameters in the period prior to an engine development event: a comparison is made with the monitoring of engine vibrations. In the conclusions, a final expressive graph makes us aware of the significant progress, over the years, achieved with the methodology here presented.
APA, Harvard, Vancouver, ISO, and other styles
6

Loyda, A., G. M. Hernández-Muñoz, L. A. Reyes-Osorio, P. Zambrano, and F. Montemayor-Ibarra. "Numerical Simulation of Rotary Forging Inconel 718 Superalloy Applied to Aeronautical Components." MRS Proceedings 1812 (2016): 101–7. http://dx.doi.org/10.1557/opl.2016.25.

Full text
Abstract:
ABSTRACTNowadays the aeronautical industry keeps strict quality standards in its dimensional specifications, mechanical properties and microstructural characteristics. Therefore, the involved manufacturing processes require keeping high standards. The nickel based superalloys are present in many components of the jet engines, being the Inconel 718MR superalloy the most common, making up to 50% of the jet engine. This is designed to resist high temperatures, corrosion and creep. The process of rotary forging is a manufacturing process that is currently under scientific and technological development in the aeronautical industry. An Avrami model coupled with a commercial FEM platform (DEFORMTM 3D) was developed to evaluate the average grain size, as a function of the working conditions at 980 °C and 1000 °C. The results provide a better understanding of the influence of temperature in the grain size evolution during the rotary forging process, compared with previous reports.
APA, Harvard, Vancouver, ISO, and other styles
7

Brouckaert, Jean-François, François Mirville, Kevin Phuah, and Peter Taferner. "Clean Sky research and demonstration programmes for next-generation aircraft engines." Aeronautical Journal 122, no. 1254 (July 9, 2018): 1163–75. http://dx.doi.org/10.1017/aer.2018.37.

Full text
Abstract:
ABSTRACTThe Clean Sky Joint Undertaking is currently managing two large-scale research and innovation programmes under FP7 and Horizon 2020 to contribute to the strengthening of the European aeronautical sector ensuring global leadership and competitiveness. This paper describes the research and demonstration programmes in Clean Sky (2008–2017) and Clean Sky 2 (2014–2024) related to propulsion technologies for the next-generation aircraft. The bulk of this work is addressed in Clean Sky 1 under the “Sustainable And Green Engines” (SAGE) programme and under the “ENGINES” programme in Clean Sky 2. The High-Level Objectives are described for each engine architecture as well as the targets in terms of CO2 and noise reduction versus a year 2000 reference unless stated otherwise. An overview of the new engine concepts that would satisfy the ACARE objectives is presented, including the main technologies which are to be developed to ensure the successful demonstration of each of those new engine concepts.
APA, Harvard, Vancouver, ISO, and other styles
8

Nakano, Toshihiro, Michael Zeutzius, Hideo Miyanishi, Toshiaki Setoguchi, and Kenji Kaneko. "Studies on Pulse Jet Engine by Wind Tunnel Testing." International Journal of Rotating Machinery 7, no. 2 (2001): 79–85. http://dx.doi.org/10.1155/s1023621x01000070.

Full text
Abstract:
Simple design and efficiency make pulse jet engines attractive for aeronautical short-term operation applications. An active control system extends the operating range and reduces the fuel consumption considerably so that this old technology might gain a new interest. The results on wind tunnel experiments have been reported together with the impact of combustion mode (pulse or steady) on system performance.
APA, Harvard, Vancouver, ISO, and other styles
9

Иванов, Антон, Anton Ivanov, Рушана Анамова, Rushana Anamova, Андрей Рипецкий, Andrey Ripetskiy, Александр Автушенко, Aleksandr Avtushenko, Александр Осипов, and Aleksandr Osipov. "Application methodology for additive technologies at the stages of prototyping airborne components and assemblies." Bulletin of Bryansk state technical university 2015, no. 2 (June 30, 2015): 8–16. http://dx.doi.org/10.12737/22847.

Full text
Abstract:
In this article described application features for additive technologies in the aeronautical industry. Application methodology for additive technologies at the stages of prototyping airborne components and assemblies is developed. Proposed methodology is appraised for manufacturing dummy engine components.
APA, Harvard, Vancouver, ISO, and other styles
10

Palano, F., F. W. Panella, and V. Dattoma. "Characterization of aeronautical engine parts welded with capacitor discharge welding technology." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 224, no. 1 (October 8, 2009): 11–22. http://dx.doi.org/10.1243/09544100jaero607.

Full text
APA, Harvard, Vancouver, ISO, and other styles
More sources

Dissertations / Theses on the topic "Aeronautical engine"

1

Valenti, Carlo Alberto. "Development of a control system for an aeronautical engine." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2019.

Find full text
Abstract:
The goal of this thesis is to develop a control system for an aeronautical engine. In particular, the engine considered is an automotive one which will be adapted for aeronautical purposes. Therefore, the engine control unit is built in Simulink®, starting from a model in LabVIEW®. The purpose of this unit is to control the engine next cycle parameters and its setpoints. Then, in order to test its effectiveness a simplified engine model is built and the whole system is tested, after a first trial of the control system. The results are presented and discussed.
APA, Harvard, Vancouver, ISO, and other styles
2

Moraru, Laurentiu Eugen. "Numerical Predictions and Measurements in the Lubrication of Aeronautical Engine and Transmission Components." University of Toledo / OhioLINK, 2005. http://rave.ohiolink.edu/etdc/view?acc_num=toledo1125769629.

Full text
APA, Harvard, Vancouver, ISO, and other styles
3

Exilard, Gorka. "Large-Eddy Simulation of constant volume combustion in a ground-breaking new aeronautical engine." Thesis, Université Paris-Saclay (ComUE), 2018. http://www.theses.fr/2018SACLC082/document.

Full text
Abstract:
Au cours des dernières années, le transport aérien de passagers connaît un développement sans cesse croissant et continue ainsi d’accroire sa contribution aux émissions mondiale de CO2. Par conséquent, un effort commun entre les avionneurs est fait pour diminuer les émissions de CO2 et de polluants. Pour encourager cet effort, les réglementations deviennent de plus en plus drastiques en terme d'émissions et de polluants tels que le CO2, les NOx mais aussi le bruit. Ces nouvelles limitations sont à la fois définies à court et moyen-long termes pour inciter les motoristes à travailler sur les technologies de plus en plus efficientes.Pour concevoir des moteurs toujours plus performants tout en respectant ces réglementations à court terme, les motoristes travaillent sur l'optimisation de leurs technologies conventionnelles, en améliorant des leviers bien identifiés comme l'augmentation du taux de compression. Cependant, cette optimisation des turbomachines actuelles a déjà atteint un niveau de maturité très élevé. Il semble ainsi difficile de continuer indéfiniment leurs optimisations. Par conséquent, pour atteindre les objectifs à moyen-long terme, les motoristes sont dès aujourd'hui en train d'étudier des nouveaux systèmes propulsifs avancés comme les chambres de Combustion à Volume Constant (CVC) qui peuvent accroître le rendement thermique. Contrairement aux chambres de combustion traditionnelles, qui fonctionnent à flux continu, les chambres CVC opèrent de façon cyclique afin de créer un volume constant pendant la phase de combustion et libérer les gaz chauds dans les étages de turbines.Pendant cette thèse, une approche numérique permettant d'évaluer ce type de chambres est développée. Tout l'enjeu est de pouvoir étudier des chambre de combustion intégrant des parties mobiles, qui permettent de créer le volume constant dédié à la combustion tout en évitant les fuites à travers ces systèmes mobiles lors de l'élévation de la pression dans la chambre. Cette modélisation doit aussi prédire correctement les phases transitoires comme l'admission des gaz frais, qui pilote la phase de combustion. Cette étude utilise des objets immergés pour modéliser les parties mobiles. Les objectifs de cette thèse sont de rendre ces objets immergés imperméables et adapter la méthode aux différents modèles utilisés pour étudier les milieux réactifs tels que le modèle de combustion ECFM-LES ou encore l'injection liquide Lagrangienne utilisée pour résoudre l'injection du fuel.Dans cette étude, une nouvelle formulation est développée puis testée sur différents cas tests de plus en plus représentatifs des chambres CVC. Cette approche numérique est ensuite évaluée sur une chambre réel étudiée expérimentalement au laboratoire PPRIRME de Poitiers. Dans cette dernière étude, deux cas non réactifs permettent de comparer les évolutions de pression à deux endroits dans la dispositif expérimental, ainsi que les champs de vitesse au sein de la chambre de combustion, aux simulations réalisées. Pour ces cas complexes, l'utilisation des objets immergés permet de prédire les résultats expérimentaux à un coût attractif.Un des cas non réactif est ensuite carburé et allumé pour confronter l'évolution pression et les champs de vitesse dans la chambre de combustion des résultats numériques obtenus aux mesures expérimentales. L'approche numérique développée a permis d’enrichir les données expérimentales, d'analyser les variabilités cycle-à-cycle rencontrées au banc et d'identifier les leviers qui permettraient d'optimiser ce type d’architecture
Over the past few years, aircrafts have become a common means of transport, thus continuously increasing their contribution to global CO2 emissions. Consequently, there is a common effort between aircraft manufacturers to reduce CO2 and pollutant emissions. To encourage this effort, regulations are becoming more and more stringent on the emissions and pollutants like CO2, NOx and noise. These regulations are both defined in the short and medium-long terms to urge aircraft manufacturers to work on more and more efficient technologies.In order to design more efficient engines while respecting the short term objectives, engine manufacturers are working on the improvement of conventional architectures by using well-known levers like the increase of the Overall Pressure Ratio (OPR). However, the optimization of the present turbomachinery has already reached a high level of maturity and it seems difficult to continuously enhance their performances. Consequently, to reach the medium-long term objectives, engine manufacturers are working on new advanced propulsion systems such as the Constant Volume Combustion (CVC) chambers, which can increase the thermal efficiency of the system. Contrary to present turbomachinery which are burning fresh gases continuously, CVC chambers operate cyclically so as to create the constant vessel dedicated to the combustion phase and to expand the burnt gases into turbine stages.In this PhD thesis, a numerical approach is developed to allow the evaluation of these kind of combustors. The challenge is to be able to evaluate CVC chambers by taking into account the moving parts which create the constant volume and avoid mass leakages through these moving parts during the increase of the combustion chamber pressure when the combustion occurs. This approach also has to correctly predict unsteady phases like the intake, which directly controls the combustion process.These moving parts are modeled with a Lagrangian Immersed Boundary (LIB) method .The main goals of this thesis is to make the LIB as airtight as possible and to render this approach compatible with the different models which are adapted to analyse reactive flows such as the ECFM-LES combustion model or Lagrangian liquid injection, used for fuel sprays. In this study, a new formulation is developed and tested on several test cases from very simple ones to cases more representative of CVC chambers.Then, this approach is evaluated on a real chamber experimentally analysed in PPRIME laboratory in Poitiers. Two non-reactive operating points are used to compare the experimental pressure at two positions in the apparatus and the experimental velocity fields in the combustion chamber with the numerical results. In this complex configuration, the LIB method allows the prediction of the experimental results with a low CPU cost. As in the experiment, one non-reactive case is carburized and ignited to compare the measured pressure and the velocity fields in the combustion chamber with the simulations. The proposed numerical approach allows the data enhancement of the experiment and then the analysis of the cycle-to-cycle variability encountered during the experimental measurements. Last but not least, this method enables the identification of the different levers that could decrease the variability and then could improve operability of this type of combustors
APA, Harvard, Vancouver, ISO, and other styles
4

Koukolíček, Ondřej. "Weather and Aeronautical Data on Map for Airplane EFB." Master's thesis, Vysoké učení technické v Brně. Fakulta informačních technologií, 2015. http://www.nusl.cz/ntk/nusl-234990.

Full text
Abstract:
Práce se zabývá webovými knihovnami pro práci s mapou a jejich možným využitím pro implementaci grafického uživatelského rozhraní nativní aplikace Weather Information Service (WIS) společnosti Honeywell. V práci jsou představeny prvky WIS, které je třeba implementovat pro úspěšné převedení aplikace do webového rozhraní. Dále jsou vysvětleny základy mapových knihoven a podrobněji popsány knihovny Leaflet a Altus Map Engine, které byly vybrány pro vytvoření demonstrační aplikace. Jedna kapitola je věnována metodám použitelným pro vykreslování ve webovém prostředí. Práce dále popisuje implementaci demonstrační aplikace, vytvořené za účelem prezentace možností mapových knihoven implementovat prvky WIS. Na závěr jsou diskutovány výhody a nevýhody obou zkoumaných knihoven a jejich použitelnost pro případné využití v aplikaci WIS.
APA, Harvard, Vancouver, ISO, and other styles
5

Notarianni, Gianmarco. "Analysis and modelling of the turbocharger behavior of an internal combustion engine for aeronautical application." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2019.

Find full text
Abstract:
The goal of this thesis project is the creation and the validation of an estimation model developed for the prediction of the Wastegate valve behaviour, to define the splitting of mass flow rate between the turbine and the bypass valve in all the operative conditions of the turbocharger system, by an analysis of the experimental data obtained from tests performed in the engine test bench of the University.
APA, Harvard, Vancouver, ISO, and other styles
6

Pavelec, Sterling Michael. "The development of turbojet aircraft in Germany, Britain, and the United States : a multi-national comparison of aeronautical engineering, 1935-1946 /." The Ohio State University, 2004. http://www.ohiolink.edu/etd/send-pdf.cgi/Pavelec%20Sterling%20Michael.pdf?acc_num=osu1082396007.

Full text
APA, Harvard, Vancouver, ISO, and other styles
7

Novikov, Yaroslav. "Development Of A High-fidelity Transient Aerothermal Model For A Helicopter Turboshaft Engine For Inlet Distortion And Engine Deterioration Simulations." Master's thesis, METU, 2012. http://etd.lib.metu.edu.tr/upload/12614389/index.pdf.

Full text
Abstract:
Presented in this thesis is the development of a high-fidelity aerothermal model for GE T700 turboshaft engine. The model was constructed using thermodynamic relations governing change of flow properties across engine components, and by applying real component maps for the compressor and turbines as well as empirical relations for specific heats. Included in the model were bleed flows, turbine cooling and heat sink effects. Transient dynamics were modeled using inter-component volumes method in which mass imbalance between two engine components was used to calculate the inter-component pressure. This method allowed fast, high-accuracy and iteration-free calculation of engine states. Developed simulation model was successfully validated against previously published simulation results, and was applied in the simulation of inlet distortion and engine deterioration. Former included simulation of steady state and transient hot gas ingestion as well as transient decrease in the inlet total pressure. Engine deterioration simulations were performed for four different cases of component deterioration with parameters defining engine degradation taken from the literature. Real time capability of the model was achieved by applying time scaling of plenum volumes which allowed for larger simulation time steps at very little cost of numerical accuracy. Finally, T700 model was used to develop a generic model by replacing empirical relations for specific heats with temperature and FAR dependent curve fits, and scaling T700 turbine maps. Developed generic aerothermal model was applied to simulate steady state performance of the Lycoming T53 turboshaft engine.
APA, Harvard, Vancouver, ISO, and other styles
8

Paolucci, Lorenzo. "High efficiency low temperature combustion in compression ignition engines for automotive and aeronautical applications." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2019.

Find full text
Abstract:
Internal combustion engines are increasingly subject to ever more stringent and severe Euro-legislations about pollutants emissions in terms of nitrogen oxide, carbon monoxide, unburned hydrocarbons and soot. In last years, thanks to advanced after treatment systems and technological innovations, emission have been improved but, due to even higher costs and complexity of such systems and in a view of further emissions restrictions, advanced combustion methods leading to cleaner and improved efficiency combustion are under investigation. A possible path to follow in order to met requirements on lower emissions, is relative to so called low temperature combustion: a group of innovative combustion methods which by exploiting lean and premixed combustion decreases significantly flame temperature which is mainly responsible for nitrogen oxide production. This work of thesis focus on preliminary study, development and experimental testing of a low temperature combustion strategy, namely "gasoline direct compression ignition" also known as "GDCI".
APA, Harvard, Vancouver, ISO, and other styles
9

Chan, KinYip. "Control algorithms for optimisation of engine combustion process with continuously changing fuel composition." Thesis, Kingston University, 2014. http://eprints.kingston.ac.uk/29888/.

Full text
Abstract:
Current research efforts in the areas of automotive control aim at developing new control algorithms so engine can work efficiently with different fuel compositions. Progressing in this direction, this thesis pioneers and researches novel control strategies to reduce the engine emissions gasses, Carbon Dioxide (CO2), Oxygen (O2), Carbon Monoxide (CO) and Nitric Oxide (NOx), while keeping optimum performance with unknown fuel mixtures. A two-zone engine combustion model is developed and thoroughly validated against the computational data from commercial engine simulation packages. The engine model is suited for the development and testing of control systems. The simulation uses the following fuel mixtures: isooctane (C8-H18), methanol (C1-H4-O1) and ethanol (C2-H6-O1). The results obtained provide better understanding of the control parameters, including fuel-to-air ratio, ignition timing, exhaust-valve timing and intake-valve timing. Moreover, the model facilitates control design. The novel engine controller is studied on the fuel composition as the additional parameter where such parameter has not been widely considered in engine control research. Efficient methodologies to estimate the original fuel composition by using the exhaust gas composition obtained from the engine are proposed and investigated. Two novel approaches based on feed-forward neural network and Adaptive Neuro-Fuzzy Interface System (ANFIS), respectively, are proposed. The portion of mixture for Isooctane-Methanol and Isooctane-Ethanol are effectively calculated. Moreover, results suggest that the feed-forward neural network outperforms the ANFIS approach and that the performance of the fuel estimator is stable in the continuous time process. Further in this research, a Multi-Input-Multi-Output (MIMO) engine control system is developed. The methodology used is a system identification employing a state-space model. In order to reduce the complexity of the state-space model, the developed AI fuel estimator is used to facilitate on the model reduction by feeding gains to controllers for the individual components. In addition, it uses the linear quadric regulator (LQR) method to find the closed-loop gain in the development of the closed-loop control system. The above techniques have been evaluated and results show that the controller is able to identify the minimum levels of the emission gases in terms of CO2, O2, CO and NOx in a continuously changing engine speed.
APA, Harvard, Vancouver, ISO, and other styles
10

Gursoy, Zeynep Ece. "A Numerical Investigation Of Helicopter Flow Fields Including Thermal Effects Of Exhaust Hot Gases." Master's thesis, METU, 2009. http://etd.lib.metu.edu.tr/upload/12611128/index.pdf.

Full text
Abstract:
This thesis investigates the flow field of a twin-engine, medium lift utility helicopter numerically. The effects of the exhaust hot gases emerging from the engines are accounted for in the numerical study. The commercial computational fluid dynamics (CFD) software ANSYS Fluent is employed for the computations. While the effects of engines are included in the computations through simple inlet and outlet boundary conditions, the main and tail rotors are simulated by the Virtual Blade Model in a time-averaged fashion. Forward flight at four different advance ratios and hover in ground effect are studied. The temperature distribution around the tail boom is compared to available flight test data. Good agreement with the flight test data is observed.
APA, Harvard, Vancouver, ISO, and other styles
More sources

Books on the topic "Aeronautical engine"

1

1907-, Whittle Frank Sir, and Gunston Bill, eds. Genesis of the jet: Frank Whittle and the invention of the jet engine. Shrewsbury, England: Airlife Publishing Ltd., 1996.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
2

Office, General Accounting. Contract pricing: Material prices overstated on T-56 engine contracts : report to the Commander, Aeronautical Systems Division, Department of the Air Force. Washington, D.C: GAO, 1986.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
3

Center), NASA-Chinese Aeronautical Establishment (CAE) Symposium (1985 NASA Lewis Research. Combustion fundamentals: NASA-Chinese Aeronautical Establishment (CAE) Symposium. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
4

Penaranda, Frank E. Aeronautical facilities catalogue. vol.2 Airbreathing propulsion and flight simulators. Washington: U.S. Office of Aeronautics and Space Technology, 1985.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
5

Marco, Manuel Lage. Hispano Suiza in Aeronautics-Men, Companies, Engines and Aircraft. Warrendale, PA: SAE International, 2003. http://dx.doi.org/10.4271/r-333.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

Pinelli, Thomas E. NASA/DoD aerospace knowledge diffusion research project.: Results of the phase 1 mail survey--propulsion and aircraft engine perspective. [Washington, D.C.]: National Aeronautics and Space Administration, 1996.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
7

Weick, Fred E. From the ground up: The autobiography of an aeronautical engineer. Washington: Smithsonian Institution Press, 1988.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
8

Askew, James W. Centaur engine Gimbal friction characteristics under simulated thrust load. [Washington, DC: National Aeronautics and Space Administration, 1986.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
9

When I consider the heavens: The spiritual quest of an aeronautical engineer. Gainesville, TX: Fair Havens Publications, 2003.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
10

Hansen, James R. Engineer in charge: A history of the Langley Aeronautical Laboratory, 1917-1958. Washington, D.C: Scientific and Technical Information Office, National Aeronautics and Space Administration, 1987.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
More sources

Book chapters on the topic "Aeronautical engine"

1

Song, Shu Fang, and Zhen Zhou Lu. "Line Sampling Reliability Analysis for Low Cycle Fatigue Life of Aeronautical Engine Disc Structure." In Fracture and Damage Mechanics V, 875–78. Stafa: Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/0-87849-413-8.875.

Full text
APA, Harvard, Vancouver, ISO, and other styles
2

Wolf, Pierre, Laurent Y. M. Gicquel, Gabriel Staffelbach, and Thierry Poinsot. "Grid Effects on LES Thermo-Acoustic Limit-Cycle of a Full Annular Aeronautical Engine." In Quality and Reliability of Large-Eddy Simulations II, 231–40. Dordrecht: Springer Netherlands, 2011. http://dx.doi.org/10.1007/978-94-007-0231-8_22.

Full text
APA, Harvard, Vancouver, ISO, and other styles
3

Xu, You Liang, Cheng Li Liu, and Zhen Zhou Lu. "Fuzzy-Random FOSM and its Application in Low Cycle Fatigue Life Reliability Analysis of an Aeronautical Engine Turbine Disk." In Fracture and Damage Mechanics V, 775–78. Stafa: Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/0-87849-413-8.775.

Full text
APA, Harvard, Vancouver, ISO, and other styles
4

Michelassi, V., F. Martelli, and F. Pigari. "Aerodynamics of Combustion Chambers for Aeronautical Engines." In Notes on Numerical Fluid Mechanics (NNFM), 162–68. Wiesbaden: Vieweg+Teubner Verlag, 1996. http://dx.doi.org/10.1007/978-3-322-89838-8_22.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

Cornu, D., A. Lenain, and R. Salapete. "Direct Manufacturing Processes for Structural Parts and Engines Design in Aeronautics." In Proceedings of the 13th World Conference on Titanium, 1527–35. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2016. http://dx.doi.org/10.1002/9781119296126.ch256.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

"Engine MDO Deployed on a Two-Stage Turbine." In Advances in Collaborative Civil Aeronautical Multidisciplinary Design Optimization, 289–330. Reston ,VA: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/5.9781600867279.0289.0330.

Full text
APA, Harvard, Vancouver, ISO, and other styles
7

"Using the Virtual-Enterprise-Collaboration Hub for Distributed Engine Optimization." In Advances in Collaborative Civil Aeronautical Multidisciplinary Design Optimization, 331–63. Reston ,VA: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/5.9781600867279.0331.0363.

Full text
APA, Harvard, Vancouver, ISO, and other styles
8

Singh, R., G. Ameyugo, and F. Noppel. "Jet engine design drivers: past, present and future." In Innovation in Aeronautics, 56–82. Elsevier, 2012. http://dx.doi.org/10.1533/9780857096098.1.56.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

Tudosie, Alexandru-Nicolae. "Aircraft Gas-Turbine Engine’s Control Based on the Fuel Injection Control." In Aeronautics and Astronautics. InTech, 2011. http://dx.doi.org/10.5772/17986.

Full text
APA, Harvard, Vancouver, ISO, and other styles
10

Kollmann, Karl, Calum E. Douglas, and S. Can Gülen. "Prelude." In Turbo/Supercharger Compressors and Turbines for Aircraft Propulsion in WWII: Theory, History and Practice—Guidance from the Past for Modern Engineers and Students, 1–7. ASME, 2021. http://dx.doi.org/10.1115/1.884676_ch1.

Full text
Abstract:
Prof. Dr.-Ing. Kollmann is one of the most important aeronautical engineers in the story of piston aeroengine development in Germany in WWII. In 12 years, Dr.-Ing. Kollmann progressed from the role of senior engineer to chief engineer of the aeroengine design department in Daimler-Benz. This book is an historical record of his own engineering work in developing high performance piston aeroengines. The original document that Dr.-Ing. Kollmann wrote in 1947 is presented here in English with extensive additional material by the authors.
APA, Harvard, Vancouver, ISO, and other styles

Conference papers on the topic "Aeronautical engine"

1

Barros, José Eduardo Mautone, Ramón Molina Valle, Cláudio Pinto De Barros, and Renato Deslandes De Figueiredo. "Design of an Aeronautical Engine Test Stand." In International Mobility Technology Conference and Exhibit. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2000. http://dx.doi.org/10.4271/2000-01-3256.

Full text
APA, Harvard, Vancouver, ISO, and other styles
2

Rouser, Kurt P., Caitlin R. Thorn, Aaron R. Byerley, Charles F. Wisniewski, Scott R. Nowlin, and Kenneth W. Van Treuren. "Integration of a Turbine Cascade Facility Into an Undergraduate Thermo-Propulsion Sequence." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-94744.

Full text
Abstract:
The Department of Aeronautics at the United States Air Force Academy utilizes a closed-loop, two-dimensional turbine cascade wind tunnel to reinforce a learning-focused undergraduate thermo-propulsion sequence. While previous work presented in the literature outlined the Academy thermo-propulsion sequence and the contextual framework for instruction, this current paper addresses how the Academy turbine cascade facility is integrated into the aeronautical engineering course sequence. Cadets who concentrate in propulsion are to some extent prepared for each successive course through their contact with the cascade, and ultimately they graduate with an exposure to experimental research that enhances their grasp of gas turbine engine fundamentals. Initially, the cascade is used to reinforce airfoil theory to all cadets in the Fundamentals of Aeronautics course. Aeronautical engineering majors take this course during the first semester of their sophomore year. The next semester all aeronautical engineering majors take Introduction to Aero-thermodynamics. In this course, the closed-loop aspect of the cascade facility is used to reinforce concepts of work addition to the flow. Heat transfer is also discussed, using the heat exchanger that regulates test section temperature. Exposure to the cascade also prepares cadets for the ensuing Introduction to Propulsion and Aeronautics Laboratory courses, taken in the junior and senior year, respectively. In the propulsion course, cadets connect thermodynamic principles to component analysis. In the laboratory course, cadets work in pairs on propulsion projects sponsored by the Air Force Research Laboratory, including projects in the cascade wind tunnel. Individual cadets are selected from the cascade research teams for summer internships, working at an Air Force Research Laboratory turbine cascade tunnel. Ultimately, cadet experiences with the Academy turbine cascade help lay the foundation for a two-part senior propulsion capstone sequence in which cadets design a gas turbine engine starting with the overall cycle selection leading to component-level design. The turbine cascade also serves to integrate propulsion principles and fluid mechanics through a senior elective Computational Fluid Dynamics course. In this course, cadets may select a computational project related to the cascade. Cadets who complete the thermo-propulsion sequence graduate with a thorough understanding of turbine engine fundamentals from both conceptual and applied perspectives. Their exposure to the cascade facility is an important part of the process. An assessment of cadet learning is presented to validate the effectiveness of this integrated research-classroom approach.
APA, Harvard, Vancouver, ISO, and other styles
3

Byerley, Aaron R., August J. Rolling, and Kenneth W. Van Treuren. "Estimating Gas Turbine Engine Weight, Costs, and Development Time During the Preliminary Aircraft Engine Design Process." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-95778.

Full text
Abstract:
This paper describes the application of a weight and cost-estimating methodology used in an undergraduate aircraft engine design course that is taught in concert with a companion course in airframe design. The two preliminary designs, one for the engine and the other for the airframe, must be integrated as subsystems within a system to satisfy the performance requirements of a given mission as outlined in a single “request for proposals”. In recent years, systems engineering management majors have been added to the design teams to work alongside the aeronautical engineering majors to analyze and report on costs, schedule, and technical risk factors in addition to the operational performance factors that have previously been the sole focus of the course. The teaming of technical management majors and aeronautical engineering majors has been driven by a heightened emphasis on system affordability. The cost-estimating methodology for gas turbine engines uses cycle parameters such as turbine rotor inlet temperature, overall pressure ratio, specific fuel consumption, level of technology, and engine dry weight as inputs. A methodology for estimating dry engine weight was developed which uses engine cycle parameters and fan face diameter as inputs in a volume analog scaling factor which was correlated against historical engine weight data. To tie all of the performance, weight, cost, and development time issues together, the paper presents an “analysis of alternatives” example that considers three different engine cycle alternatives. The design tools presented in this paper will provide a strong foundational understanding of how to systematically weigh and evaluate the important tradeoffs between aircraft turbofan engine performance, cost, schedule, and risk factors. Equipping students with the insight and ability to perform these multidisciplinary trade studies during the preliminary engine design process is this paper’s most important contribution.
APA, Harvard, Vancouver, ISO, and other styles
4

SAMI, MOH D. "Modeling of 12 Cylinder Camless Engine with Neural Networks." In Fifth International Conference On Advances in Mechanical, Aeronautical and Production Techniques - MAPT 2016. Institute of Research Engineers and Doctors, 2016. http://dx.doi.org/10.15224/978-1-63248-090-3-44.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

Andriani, Roberto, Liliana Ferri, and Umberto Ghezzi. "Thermodynamic study of an adiabatic piston engine with heat recovery for aeronautical application." In 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-3482.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

Lhommeau, T., R. Meuret, and M. Karama. "Technological study of an IGBT module for an aeronautical application in zone engine." In 2005 IEEE 11th European Conference on Power Electronics and Applications. IEEE, 2005. http://dx.doi.org/10.1109/epe.2005.219735.

Full text
APA, Harvard, Vancouver, ISO, and other styles
7

ZUSSY, TIMOTHEE. "Characterization method of engine air behaviour from a real head cylinder." In Seventh International Conference On Advances in Mechanical, Aeronautical and Production Techniques - MAPT 2017. Institute of Research Engineers and Doctors, 2017. http://dx.doi.org/10.15224/978-1-63248-129-0-45.

Full text
APA, Harvard, Vancouver, ISO, and other styles
8

RAVICHANDRA, D., K. ABHISHEK, K. VIJAYA, and RAVI KUMAR. "Investigation on a CI Engine Fuelled with blends of Waste Tyre oil." In Third International Conference on Advances in Mechanical, Aeronautical and Production Techniques - MAPT 2015. Institute of Research Engineers and Doctors, 2015. http://dx.doi.org/10.15224/978-1-63248-059-0-70.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

SENTHIIL, P. V., V. S. AAKASH, and V. S. MIRUDHUNEKA. "Analysis Of Oxygen Enriched Combustion Technology In A Single Cylinder Di Diesel Engine." In Second International Conference on Advances in Mechanical, Aeronautical and Production Techniques - MAPT 2014. Institute of Research Engineers and Doctors, 2014. http://dx.doi.org/10.15224/978-1-63248-037-8-90.

Full text
APA, Harvard, Vancouver, ISO, and other styles
10

Rolling, August J., Aaron R. Byerley, and Charles F. Wisniewski. "Integrating Systems Engineering Into the USAF Academy Capstone Gas Turbine Engine Course." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-46440.

Full text
Abstract:
This paper is intended to serve as a template for incorporating technical management majors into a traditional engineering design course. In 2002, the Secretary of the Air Force encouraged the USAF Academy to initiate a new interdisciplinary academic major related to systems engineering. This direction was given in an effort to help meet the Air Force’s growing need for “systems” minded officers to manage the development and acquisition of its ever more complex weapons systems. The curriculum for the new systems engineering management (SEM) major is related to the “engineering of large, complex systems and the integration of the many subsystems that comprise the larger system” and differs in the level of technical content from the traditional engineering major. The program allows emphasis in specific cadet-selected engineering tracks with additional course work in human systems, operations research, and program management. Specifically, this paper documents how individual SEM majors have been integrated into aeronautical engineering design teams within a senior level capstone course to complete the preliminary design of a gas turbine engine. As the Aeronautical engineering (AE) cadets performed the detailed engine design, the SEM cadets were responsible for tracking performance, cost, schedule, and technical risk. Internal and external student assessments indicate that this integration has been successful at exposing both the AE majors and the SEM majors to the benefits of “systems thinking” by giving all the opportunity to employ SE tools in the context of a realistic aircraft engine design project.
APA, Harvard, Vancouver, ISO, and other styles
You might also be interested in the extended bibliographies on the topic 'Aeronautical engine' for particular source types:
Journal articles Dissertations / Theses Books
We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!

To the bibliography