Tesis sobre el tema "Turbine engines materials"
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Temple, Benjamin John. "Advancements of Gas Turbine Engines and Materials". OpenSIUC, 2020. https://opensiuc.lib.siu.edu/theses/2763.
Texto completoCornwell, Michael. "Causes of Combustion Instabilities with Passive and Active Methods of Control for practical application to Gas Turbine Engines". University of Cincinnati / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1307323433.
Texto completoRoth, Richard. "Materials substitution in aircraft gas turbine engine applications". Thesis, Massachusetts Institute of Technology, 1992. http://hdl.handle.net/1721.1/13112.
Texto completoSaari, Henry M. J. "The processing of gas turbine engine hot section materials through directional solidification". Thesis, National Library of Canada = Bibliothèque nationale du Canada, 2000. http://www.collectionscanada.ca/obj/s4/f2/dsk1/tape4/PQDD_0018/MQ48472.pdf.
Texto completoSaari, Henry M. J. Carleton University Dissertation Engineering Mechanical and Aerospace. "The Processing of gas turbine engine hot section materials through directional solidification". Ottawa, 1999.
Buscar texto completoEveritt, Stewart. "Developments in advanced high temperature disc and blade materials for aero-engine gas turbine applications". Thesis, University of Southampton, 2012. https://eprints.soton.ac.uk/348897/.
Texto completoGhulam, Mohamad. "Characterization of Swirling Flow in a Gas Turbine Fuel Injector". University of Cincinnati / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1563877023803877.
Texto completoDsouza, Jason Brian. "Numerical Analysis of a Flameless Swirl Stabilized Cavity Combustor for Gas Turbine Engine Applications". University of Cincinnati / OhioLINK, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1627663015527799.
Texto completoSahay, Prateek. "Development of a Robotic Cell for Removal of Tabs from Jet Engine Turbine Blade". University of Cincinnati / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1574417686354007.
Texto completoAull, Mark J. "Comparison of Fault Detection Strategies on a Low Bypass Turbofan Engine Model". University of Cincinnati / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1321368833.
Texto completoBohun, Michael H. "Several Non-Destructive Inspection Methods Applied to Quantify Fretting Fatigue Damage in Simulated Ti-6Al-4V Turbine Engine Dovetail Components". University of Dayton / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1332421987.
Texto completoPanakarajupally, Ragavendra Prasad. "DEVELOPMENT OF A UNIQUE EXPERIMENTAL FACILITY TO CHARACTERIZE THE FATIGUE AND EROSION BEHAVIOR OF CERAMIC MATRIX COMPOSITES UNDER TURBINE ENGINE CONDITIONS". University of Akron / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=akron1605615829736275.
Texto completoTERNER, MATHIEU. "Innovative materials for high temperature structural applications: 3rd Generation γ-TiAl fabricated by Electron Beam Melting". Doctoral thesis, Politecnico di Torino, 2014. http://hdl.handle.net/11583/2527509.
Texto completoBonilla, Carlos Humberto. "The Effect of Film Cooling on Nozzle Guide Vane Ash Deposition". The Ohio State University, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=osu1353961326.
Texto completoSadinski, Robert J. "The High Pressure Rheological Response of SAE AS 5780 HPC, MIL-PRF-23699 HTS, and DOD-PRF-85734 Lubricants". University of Akron / OhioLINK, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=akron1627035576924735.
Texto completoDas, Saurabh Mohan. "Improvement of High Temperature Oxidation Behavior of ‘w’ Free Y strengthened Co-based Superalloys through Alloying Addition". Thesis, 2019. https://etd.iisc.ac.in/handle/2005/4425.
Texto completoFitzpatrick, John Nathan. "Coupled thermal-fluid analysis with flowpath-cavity interaction in a gas turbine engine". Thesis, 2013. http://hdl.handle.net/1805/4441.
Texto completoThis study seeks to improve the understanding of inlet conditions of a large rotor-stator cavity in a turbofan engine, often referred to as the drive cone cavity (DCC). The inlet flow is better understood through a higher fidelity computational fluid dynamics (CFD) modeling of the inlet to the cavity, and a coupled finite element (FE) thermal to CFD fluid analysis of the cavity in order to accurately predict engine component temperatures. Accurately predicting temperature distribution in the cavity is important because temperatures directly affect the material properties including Young's modulus, yield strength, fatigue strength, creep properties. All of these properties directly affect the life of critical engine components. In addition, temperatures cause thermal expansion which changes clearances and in turn affects engine efficiency. The DCC is fed from the last stage of the high pressure compressor. One of its primary functions is to purge the air over the rotor wall to prevent it from overheating. Aero-thermal conditions within the DCC cavity are particularly challenging to predict due to the complex air flow and high heat transfer in the rotating component. Thus, in order to accurately predict metal temperatures a two-way coupled CFD-FE analysis is needed. Historically, when the cavity airflow is modeled for engine design purposes, the inlet condition has been over-simplified for the CFD analysis which impacts the results, particularly in the region around the compressor disc rim. The inlet is typically simplified by circumferentially averaging the velocity field at the inlet to the cavity which removes the effect of pressure wakes from the upstream rotor blades. The way in which these non-axisymmetric flow characteristics affect metal temperatures is not well understood. In addition, a constant air temperature scaled from a previous analysis is used as the simplified cavity inlet air temperature. Therefore, the objectives of this study are: (a) model the DCC cavity with a more physically representative inlet condition while coupling the solid thermal analysis and compressible air flow analysis that includes the fluid velocity, pressure, and temperature fields; (b) run a coupled analysis whose boundary conditions come from computational models, rather than thermocouple data; (c) validate the model using available experimental data; and (d) based on the validation, determine if the model can be used to predict air inlet and metal temperatures for new engine geometries. Verification with experimental results showed that the coupled analysis with the 3D no-bolt CFD model with predictive boundary conditions, over-predicted the HP6 offtake temperature by 16k. The maximum error was an over-prediction of 50k while the average error was 17k. The predictive model with 3D bolts also predicted cavity temperatures with an average error of 17k. For the two CFD models with predicted boundary conditions, the case without bolts performed better than the case with bolts. This is due to the flow errors caused by placing stationary bolts in a rotating reference frame. Therefore it is recommended that this type of analysis only be attempted for drive cone cavities with no bolts or shielded bolts.
Petley, Vijay Uttamrao. "Material and Mechanical Aspects of Thin Film Coatings for Strain Sensing Application on Aero Engines". Thesis, 2017. http://etd.iisc.ac.in/handle/2005/4273.
Texto completoAlam, MD Zafir. "Tensile Behavior Of Free-Standing Pt-Aluminide (PtAl) Bond Coats". Thesis, 2012. https://etd.iisc.ac.in/handle/2005/2531.
Texto completoAlam, MD Zafir. "Tensile Behavior Of Free-Standing Pt-Aluminide (PtAl) Bond Coats". Thesis, 2012. http://hdl.handle.net/2005/2531.
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