Aerodynamic optimization of ram air turbine rotor of a commercial aircraft /

dc.contributor.authorÁvila Zayas, Mariana Glenda
dc.contributor.codirectorDurazo Romero, Emmanuel Santiago
dc.contributor.directorSiqueiros Hernández, Miriam Avital, Eldad
dc.coverage.placeofpublicationMexicali, Baja California. Autónoma de Baja California, Facultad de Ingenierí­a University of London. Queen Mary de Maestría / master Thesis.í­a y Doctorado en Ciencias e Ingenierí­a
dc.description.abstractRam Air Turbines (RATs) are employed to supply power for auxiliary and backup systems of an aircraft in case of a major power shortage. These turbines are commonly Horizontal Axis Wind Turbines (HAWTs). In this study, we investigate the performance of a RAT under cruise altitude operating conditions. CFD-RANS computations coupled with Blade Element Method (BEM) are conducted to examine the impact of adding Gurney flaps (GF) to the rotor blades in terms of power and drag (thrust) performance. Three different GF height configurations of 1% chord (1%c), 3%c, and 5%c are applied to the blades of a small RAT. The rotor diameter is 1.016 meters, comprising of two blades with a constant chord length of 0.127 meters and a NACA 8318 airfoil, featuring twist angle along the blade span. The effects of the Gurney flaps are explored over a Reynolds number range of 200k to 500k based on the chord length, corresponding to the Reynolds number of the relative wind speed around the blade at sections of 25%, 50%, 75% and 100% of the blade. Lift coefficient (CL) and drag coefficient (CD) results were imported to Qblade to perform a BEM turbine analysis. The results demonstrate a noticeable increase in the maximum coefficient of power around tip speed ratio (TSR) of 3. Also, a comparison was made between a clean blade and a blade with GF mounted only at the root of the blade. The blade with GF representing 1% of the chord, mounted at the root of the blade yields improved CP/CT for a wider range of 3< TSR <6.6. However, a GF with height of 5%c exhibits the highest CP/CT ratio, both at low TSR (ranging from 1 to 1.8) and high TSR (from 4 to 7.6). Data validation was conducted for the NACA 8318 airfoil using experimental results from Yoshida (2000). Additionally, data validation was also performed by comparing the findings with CFD data from Shen (2016) for E387 airfoil performed on the low-speed wind tunnel of Queen Mary University of London. These validations aim to support and validate the results obtained within this thesis.
dc.format.extent86 p. il.
dc.publisherUniversidad Autónoma de Baja California.
dc.subjectAerodinámica||Tesis y disertaciones académicas.||lemb||Aviones||Tesis y disertaciones académicas.||lemb||Aerodinámica Matemáticas||Tesis y disertaciones académicas||lemb
dc.subject.lccTL570 A85 2023
dc.titleAerodynamic optimization of ram air turbine rotor of a commercial aircraft /
dc.uabc.bibliographycNoteIncluye referencias bibliográficas
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