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000			02893ntm a2200241 a 4500
001			vtls000072782
003			KUKTEM
005			20251114204547.0
008			130627t2012 my da f m 000 0 eng d
020			_aTHE0007388(Local)
039		9	_a201905151141 _bfawwaz _y201306271549 _zhuda
040			_aUMP
090			_aTL709 .R53 2012 rs Bc.
100	0		_aMohamad Ridhwan Raja Mohd
245	1	0	_aDesign, fabrication and testing of small scale turbine jet engine / _cMohamad Ridhwan Raja Mohd
260			_aKuantan, Pahang : _bUMP, _c2012
300			_axvii, 79 p. : _bill. (some col.) ; _c30 cm. + _e1 CD-ROM
502			_aProject Paper (Bachelor of Mechanical Engineering with Automotive) -- Universiti Malaysia Pahang - 2012
504			_aBibliography : p. 66-67
520	3		_aA turbine jet engine comprises of four main parts, which are a compressor, a combustion chamber, a turbine and an exhaust nozzle. Turbine jet engine operates at an open cycle called a jet propulsion cycle. A small-scale turbine jet engine comprises of the same element as the gas-turbine engine but in a smaller scale. Both engines differ in utilization and purpose of its production. Turbine jet engines were constructed mainly for air transportation while the small-scale turbine jet engines are developed for a wider purpose, ranging for research activity to hobbyist enthusiastic. Hence, this thesis encompasses the design, fabrication, and testing a small-scale turbine jet engine. The engine was derived from an automobile turbocharger, which provided the turbine and compressor component. A combustion chamber was design and fabricated. Engine support system comprised of ignition, lubrication and fuel delivery system were installed at the engine. The engine assembly was mounted in a test setup. Thermocouples were installed at three different stations on the engine flow path to measure the temperature. Fuel regulators were utilized to measure the fuel flow. The engine was started using a specific procedure until it self-sustained. During testing, the engine was only able to self-sustain approximated for 10 seconds at kg/s fuel mass flow rate. Troubleshooting and analysis regarding the failure of the engine was done. Analysis shows that there are four possible factors involves, namely, the uses of LPG fuel, large pressure drop at the exit of combustion chamber, low pressure pump and leaking at the turbocharger. Four recommendations were made for further studies, which are, utilize a brand-new turbocharger for the engine, use a pure propane gas as a source of fuel, avoid uses of pipe flange at the combustion chamber and utilize a higher pressure pump for lubrication system. Further modification was not made due to time and cost limitation.
650		0	_aJet engines _xDesign and construction
999			_aVIRTUA40 _c4133 _d4139
999			_aVTLSSORT0080020004000900100024502600300050205040520065009992