CBL - Campus del Baix Llobregat

Projecte llegit

Títol: Pitot tube design for total pressure determination at the high-temperature stages of a micro-turbojet

Estudiants que han llegit aquest projecte:

Director/a: MELLIBOVSKY ELSTEIN, FERNANDO PABLO

Departament: FIS

Títol: Pitot tube design for total pressure determination at the high-temperature stages of a micro-turbojet

Data inici oferta: 27-01-2025     Data finalització oferta: 27-09-2025


Estudis d'assignació del projecte:
    GR ENG SIST AEROESP
Tipus: Individual
 
Lloc de realització: EETAC
 
Paraules clau:
Pitot tube, small-scale turbojet engine, computational fluid dynamics, compressible flow, turbulent flow, meshing, material selection, thermal analysis
 
Descripció del contingut i pla d'activitats:
 
Overview (resum en anglès):
This bachelor's thesis assesses the design of a total pressure probe intended for the exhaust section of a small-scale turbojet engine. The main objective is to develop a simple yet reliable probe capable of operating under high-temperature and high-velocity conditions. The project consists of a computational fluid dynamics (CFD) study performed with OpenFOAM, a material and process selection, based on Michael F. Ashby's methodology and a thermal analysis carried out with SolidWorks. Through a parametric study, the influence of different geometric configurations on the measurement accuracy was evaluated as a function of the Mach number and the angle of incidence. The outcome of these analyses indicates that a bevelled-probe made of AISI 310 stainless steel, characterized by a 20º aperture angle and a 0.2 inner-to-outer diameter ratio provides the best compromise between accuracy, simplicity, structural integrity and manufacturability. The range for which the probe was shown to keep acceptable accuracy was within an angle of incidence from 0º to 30º. Moreover, the accuracy at larger angles of incidence was found to deteriorate faster at higher Mach numbers. Additionaly, the thermal analysis ensured safe operation of the external components connected to the probe. The final model provides an alternative probe for environments where high-speed, high-temperature and a certain degree of flow deviation may occur, such as academic and experimental small-scale turbojet engine testing.

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