Razvoj eksperimentalne proge za demonstracijo delovanja didaktičnega turbinskega motorja

Jerak, Matej (author), Žvar Baškovič, Urban (mentor), Katrašnik, Tomaž (comentor)

V zaključni nalogi je bila zasnovana, izdelana ter testno zagnana in umerjena eksperimentalna proga za demonstracijo delovanja letalskega turbinskega motorja. Prvi delo diplomskega delo opisuje celovito zasnovo eksperimentalne proge, ki vključuje določitev merjenih parametrov in izbiro primernega turbinskega motorja ter vse merilne infrastrukture. V drugi fazi je predstavljena zasnova in izdelava po meri izdelanih komponent, ki so omogočile namestitev merilnih zaznaval na ohišje turbinskega motorja. V tretji fazi je diplomskega dela je opisan proces testnega zagona, umerjanja merilnega zaznavala potisne sile ter merilnika masnega toka zraka in izvedba končnih meritev v različnih obratovalnih točkah. Turbinski motor je dosegel največjo potisno silo 94,03 N pri 154000 vrtljajih motorja na minuto in masnem toku goriva 0,00508 kg/s.

• Language: Slovenian
• Keywords: turbinski motorji, merilna infrastruktura, statični tlaki, dinamični tlak, sila potiska, izstopne temperature, masni tok goriva
• Work type: Bachelor thesis/paper
• Typology: 2.11 - Undergraduate Thesis
• Organization: FS - Faculty of Mechanical Engineering
• Year: 2025
• Number of pages: XVIII, 59 str.
• PID: 20.500.12556/RUL-171914
• UDC: 621.452.3:531.3(043.2)
• COBISS.SI-ID: 248613635
• Publication date in RUL: 04.09.2025

Secondary language

• Language: English
• Title: Development of an experimental test bench for demonstrating the operation of a didactic turbine engine

Abstract

In this thesis, an experimental test rig for demonstrating the operation of an aircraft gas turbine engine was designed, manufactured, test-run, and calibrated. The first part of the thesis describes the complete design of the experimental rig, including the determination of the measured parameters and the selection of a suitable turbine engine as well as all associated measurement infrastructure. The second phase presents the design and fabrication of custom-made components that enabled the installation of measurement sensors onto the turbine engine casing. The third phase describes the process of the test run, the calibration of the thrust force sensor and the air mass flow meter, and the execution of final measurements at various operating points. The turbine engine achieved a maximum thrust of 94,03 N at 154000 revolutions per minute, with a fuel mass flow rate of 0,00508 kg/s.

• Keywords: experimental test bench, measurement infrastructure, static pressure, dynamic pressure, thrust force, outlet temperature, fuel mass flow