Projecte llegit
Títol: Data acquisition system and bellmouth intake design for microturbojet test bench
Estudiants que han llegit aquest projecte:
BILBAO AJURIAGUERRA, GALDER (data lectura: 18-07-2025)- Cerca aquest projecte a Bibliotècnica
BILBAO AJURIAGUERRA, GALDER (data lectura: 18-07-2025)- Cerca aquest projecte a Bibliotècnica
BILBAO AJURIAGUERRA, GALDER (data lectura: 18-07-2025)
BILBAO AJURIAGUERRA, GALDER (data lectura: 18-07-2025)Director/a: MELLIBOVSKY ELSTEIN, FERNANDO PABLO
Departament: FIS
Títol: Data acquisition system and bellmouth intake design for microturbojet test bench
Data inici oferta: 27-01-2025 Data finalització oferta: 27-09-2025
Estudis d'assignació del projecte:
DG ENG AERO/SIS TEL
| Tipus: Individual | |
| Lloc de realització: EETAC | |
| Segon director/a (UPC): SERRANO FINETTI, ERNESTO | |
| Paraules clau: | |
| Microturbojet, data acquisition, CFD, bellmoth and sensors. | |
| Descripció del contingut i pla d'activitats: | |
| Overview (resum en anglès): | |
| This thesis presents the design and creation of a bellmouth intake system and a data acquisition system capable of assessing and monitoring key parameters of a microturbojet. The reference microturbojet is the EvoJet B170 Neo, which is capable of generating up to 170 N of thrust.
The data acquisition system and the bellmouth have been developed with the aim of creating an experimental and educational tool for the Escola d'Enginyeria de Telecomunicació y Aeroespacial de Castelldefels (EETAC). The bellmouth has been designed and validated through 2D and 3D CFD simulations, evaluating the performance at idle, cruise and max power conditions. Additionally, the sensitivity of the measurements to perturbations introduced by the struts, the engine receptacle and the crosswind was evaluated. These simulations have confirmed that the flow enter uniformly and stably, without boundary layer separation. The data acquisition system has been developed with commercial components such as the ESP32-S3, ADS1115 and temperature, pressure, load cell and flowmeter sensors integrated into a PCB fabricated at the university. The acquisition system permits the measurement of total and static pressure, key temperatures, fuel consumption and thrust through a load cell. The acquisition system has been tested in laboratory and real conditions with the engine ignited. The data acquisition system will remain at the university, available for future improvements and investigations, and will serve as a platform for academic projects related to propulsion, instrumentation, or aerodynamic design. |
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