Publication: Investigating the relation of high temperature biofuel combustion with gas turbine rotor blade structure at increasing shaft speeds using fluid-structure interaction
| datacite.subject.fos | oecd::Engineering and technology::Mechanical engineering::Aerospace engineering | |
| dc.contributor.author | Noorashid, Muhammad Noorakmal | |
| dc.date.accessioned | 2024-11-26T09:19:41Z | |
| dc.date.available | 2024-11-26T09:19:41Z | |
| dc.date.issued | 2024-07-01 | |
| dc.description.abstract | This study investigates the correlation between biofuel combustion temperature and the structural integrity of the high-pressure turbine (HPT) blade in an aircraft engine, examining the effects across a range of increasing shaft speeds from 8400 rpm to 10, 400 rpm. The biofuels were Jatropha Bio-synthetic Paraffinic Kerosene (JSPK) and Camelina Bio-synthetic Paraffinic Kerosene (CSPK). The fuels were tested as pure fuels and blended with Jet-A. The study was first performed by simulating the fuels in a Gas Turbine Simulation Program (GSP11) to evaluate changes in the thermodynamic properties of gas turbine engine components, particularly at the turbine. The results obtained served as input parameters for the boundary condition of the turbine blade model simulated in computational fluid dynamics (CFD) to visualize the flow behavior around the turbine blade. Fluid-Structure Interaction (FSI) approach is then used to analyse the impact on the turbine blade structure. For the same engine parameters, the results from GSP11 revealed a linear correlation between temperature and pressure across the gas turbine components with shaft speeds. Combusting biofuels produced lower temperatures and pressures than Jet-A, resulting in a lower engine thrust. Also, at all shaft speeds, the fuel flow and thrust specific fuel consumption (TSFC) of biofuels was 1% to 3% lower than that of Jet-A, indicating that the engine thrust improved while consuming less fuel. The combustion temperature and pressure reduction of biofuels contribute to the lower thermomechanical loading exerted on the turbine rotor blades. At all ranges of shaft rotational speed, utilizing biofuel as a blend leads to reductions of up to 0.047% to 0.232% in blade deformation, 0.045% to 0.116% in stress, and 0.076% to 0.274% in strain, ultimately improving the fatigue life cycles of the rotor blade by up to 0.274% to 0.699%. The reduction becomes more significant when pure CSPK and JSPK are utilized. This study serves as a preliminary analysis of the advantages of utilizing biofuels in the component structures of aircraft engines. | |
| dc.identifier.uri | https://erepo.usm.my/handle/123456789/20817 | |
| dc.language.iso | en | |
| dc.title | Investigating the relation of high temperature biofuel combustion with gas turbine rotor blade structure at increasing shaft speeds using fluid-structure interaction | |
| dc.type | Resource Types::text::thesis::master thesis | |
| dspace.entity.type | Publication | |
| oairecerif.author.affiliation | Universiti Sains Malaysia |