The effect of combustor Inlet Swirl on the performance of a micro gas turbine
| dc.contributor.advisor | Van der Spuy, S. J. | en_ZA |
| dc.contributor.author | Ferreira, Lourens Jan | en_ZA |
| dc.contributor.other | Stellenbosch University. Faculty of Engineering. Dept. of Mechanical and Mechatronic Engineering. | en_ZA |
| dc.date.accessioned | 2020-11-26T14:52:12Z | |
| dc.date.accessioned | 2021-01-31T19:44:25Z | |
| dc.date.available | 2020-11-26T14:52:12Z | |
| dc.date.available | 2021-01-31T19:44:25Z | |
| dc.date.issued | 2020-12 | |
| dc.description | Thesis (MEng)--Stellenbosch University, 2020. | en_ZA |
| dc.description.abstract | ENGLISH ABSTRACT: The effects of combustor inlet swirl on the performance of the BMT120KS micro gas turbine engine is evaluated both experimentally and numerically in this thesis. The temperature variation at the exhaust of the engine and the air mass flow rate is included in this evaluation. The turbine engine was numerically modelled using NUMECA FINE/Turbo and the cold flow inlet conditions at the combustor inlet was determined. The experimental results achieved a maximum standard deviation of 2% for the various measured parameters. The study shows that the existing temperature measurement system overpredicts the temperature value by about 50 °C in comparison to a more accurately measured outlet temperature value. The existing control temperature matches the maximum temperature experienced by the turbine within 25 °C. The air mass flow rate measurement system is investigated and compared with previous studies and numerical data. The bell mouth pressure transducer is replaced and revised pressure readings are used to establish a revised mass flow rate that approximates referenced numerical data within 12% compared to an initial 40%. Finally it found that the inlet swirl has a definite effect on the performance of a MGT. The 30° de-swirler configuration shows a 24% thrust increase at the same SFC levels as the 0° configuration for 90 000 rpm while the 45° de-swirler configuration shows a 12% thrust decrease with an 11% increase in SFC levels compared to the 0° configuration at 90 000 rpm. Further testing should be done to find the optimal swirl conditions for the various operational speeds of the BMT120KS. | en_ZA |
| dc.description.abstract | AFRIKAANSE OPSOMMING: Die gevolg van die verandering in die luginvalshoek stroomop van die verbrandingskamer op die werksverrigting van die BMT120KS mikro gasturbine, word eksperimenteel en numeries geévalueer in hierdie studie. Die akkurate meting van die temperatuurvariasie in die uitlaatgas van die gasturbine en die bepaling van die lugmassavloei deur die gasturbine, vorm deel van die studie. Die studie bevind dat die luginvalshoek na die vebrandingskamer 'n definitiewe uitwerking op die wersksverrigting van die gasturbine het. Die studie bewys dat die bestaande temperatuurmeting van die uitlaatgas 50 °C meer is in vergelyking met die gemiddelde uitlaatgas temperatuur van die turbine. Die bestaande temperatuurmeting plaas die maksimum temperature in die gasturbine binne 25 °C. Die meting van die lugmassavloei deur die turbine is ook verbeter en is met numeriese data van vorige studies vergelyk. Die die bestaande sisteem is vervang met 'n meer akkurate instrument en die nuwe lugmassavloei is binne 12% van die verwysing numeriesie waardes, 'n verbetering op die vorige waarde van 40%. Die optimale luginvalshoek vir die spesi eke verbrandingskamer is nie bepaal nie; die studie wys wel dat die 30° vloeirigter konfigurasie 24% meer stukrag bied by dieselfde spesifieke brandstofverbruik as die 0° konfigurasie by 90 000 opm. Die 45° vloeirigter konfigurasie wys 'n 12% vermindering in stikrag tesame met 'n 11% toename in spesifieke brandstofverbruik teenoor die 0° konfigurasie by 90 000 opm. Additionele eksperimentele werk moet gedoen word om die optimale luginvalshoek vir die verbandingskamer by verskillende bedryfsnelhede van die turbine te bepaal. | af_ZA |
| dc.description.version | Masters | en_ZA |
| dc.format.extent | 112 pages | en_ZA |
| dc.identifier.uri | http://hdl.handle.net/10019.1/109316 | |
| dc.language.iso | en_ZA | en_ZA |
| dc.publisher | Stellenbosch : Stellenbosch University | en_ZA |
| dc.rights.holder | Stellenbosch University | en_ZA |
| dc.subject | Turbines | en_ZA |
| dc.subject | Micro gas Turbine (MGT) | en_ZA |
| dc.subject | Exhaust gas temperature (EGT) | en_ZA |
| dc.subject | UCTD | en_ZA |
| dc.subject | Combustors, Gas-turbine | en_ZA |
| dc.title | The effect of combustor Inlet Swirl on the performance of a micro gas turbine | en_ZA |
| dc.type | Thesis | en_ZA |