Zasnova sistema za bremenjenje pomožne pogonske enote letala

diplomsko delo Visokošolskega strokovnega študijskega programa I. stopnje Strojništvo

Žan Merc (Author), Tine Seljak (Mentor), Amor Chowdhury (Co-mentor)

Abstract

Vloga pomožne pogonske enote v letalih je predvsem zagotavljanje komprimiranega zraka za potrebe zagona glavnih motorjev in zagotavljanje električne energije, kadar glavni motorji niso v obratovanju. S ciljem defosilizacije letalskega sektorja se tudi pomožne pogonske enote razvijajo v smeri uporabe nizko-ogljičnih goriv, kar pa zahteva preizkušanje v nadzorovanem laboratorijskem okolju in s tem tudi zagotavljanje ustreznega odjema moči. V diplomski nalogi je obravnavan turbogredni motor GTCP85-98D, ki predstavlja pomožno pogonsko enoto letala. Sposoben je proizvodnje električne energije napetosti 120 V in frekvence 400 Hz ter komprimiranega zraka. Na podlagi izračunane energijske bilance motorja, ki je osnovana na podatkih, razpoložljivih v dokumentaciji ter analize načinov delovanja pomožne pogonske enote, so v diplomski nalogi predstavljene različne topologije sistemov za bremenjenje motorja. Sistemi za bremenjenje so ovrednoteni s stališča primernosti za uporabo, v raziskovalne namene ter tudi z vidika investicije in uvedbe morebitnih podpornih sistemov. Na osnovi izračunov je kot najprimernejša identificirana rešitev z uporabo prehodnega shranjevalnika energije, ki omogoča manjše priključne moči, hkrati pa zadošča za večurno delovanje pomožne pogonske enote pri polni moči.

Keywords

diplomske naloge;pomožna pogonska enota;energijska bilanca;turbinski motorji;generatorji;obremenitev;

Data

Language:	Slovenian
Year of publishing:	2020
Typology:	2.11 - Undergraduate Thesis
Organization:	UL FS - Faculty of Mechanical Engineering
Publisher:	[Ž. Merc]
UDC:	621.452:629.7(043.2)
COBISS:	17058075
Views:	817
Downloads:	200
Average score:	0 (0 votes)
Metadata:

Other data

Secondary language:	English
Secondary title:	Design of the airplane auxiliary power unit loading system
Secondary abstract:	The main role of the auxiliary power unit in airplanes is to provide bleed air for the purposes of launching the main engines and to provide electricity when the main engines are not in operation. With the aim of defossilising the aviation sector, auxiliary power units are as well being developed in the way of using low-carbon fuels, which requires experimenting in a controlled laboratory environment and thus ensuring adequate power consumption. In the final thesis, a turboshaft engine GTCP85-98D is discused as it represents the auxiliary power unit of the airplane. It is capable of producing 120 V and 400 Hz of the electrical energy and also bleeds air. Based on the calculated energy balance of the engine, which is established due to the information available in the documentation and the analysis of the way how the auxiliary power unit works, the final thesis represents different topologies of the engine loading systems. The loading systems are estimated to be suitable for usage, research, and investment and introduction of possible support systems, as well. On the basis of the calculations, the most appropriate identified solution is the usage of a DC battery as it allows smaller connection capacities, while it is also sufficient for the auxiliary power unit to operate on its full power for several hours.
Secondary keywords:	auxiliary power unit;energy balance;turbine engines;generators;load;
Type (COBISS):	Bachelor thesis/paper
Study programme:	0
Embargo end date (OpenAIRE):	1970-01-01
Thesis comment:	Univ. v Ljubljani, Fak. za strojništvo
Pages:	XXIV, 63 str.
ID:	11411842