Performance characteristics monitoring of turboprop engine for the development of preliminary requirement of an engine testing facility

Mohd Yunos, Siti Nur Mariani (2011) Performance characteristics monitoring of turboprop engine for the development of preliminary requirement of an engine testing facility. Masters thesis, Universiti Tun Hussein Onn Malaysia.

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Abstract

Faculty of Mechanical and Manufacturing Engineering, Universiti Tun Hussein Onn Malaysia (UTHM) has acquired a Pratt and Whitney PT6A-20 turboprop engine to be used in its aeronautical engineering technology programme. However, to fully utilize the engine, a solid familiarity with its current performance and a proper testing arrangement are important. The main concern on the engine is the age of the engine and lack of information on its previous performance. Therefore, in this study, the actual performance of this turboprop engine was evaluated experimentally. The performance evaluation is also important for the development , ,- , of preliminary requirements for the engine test cell. A better performance , , investigation and testing can be conducted in an engine test cell. Altogether, a total of three engine tests were performed by varying engine speed from 55 percent rpm to 75 percent rpm. Performance data obtained include the engine's torque, propeller speed, fuel flow rate, and inter-turbine temperature. They were captured by using data acquisition software from AeroTrain Corp. An averaging was done to the data in order to study engine shaft horsepower, specific fuel consumption, and thermal efficiency. From the result of manual calculation, the engine can produce power up to 34.8 kW while running at 75 percent rpm. The specific fuel consumption is 7.07 kgikW-hr while the thermal efficiency is at 1.19 percent. On the other hand, the data acquisition system shows that the engine managed to deliver 89.5 kW of power, 3.15 kg/kW-hr of specific fuel consumption and thermal efficiency of 19.5 percent. It was found that the results of manual calculation were significantly lower than the one obtained using the software with 88 percent different in shaft horsepower and 77 percent different in specific fuel consumption. Although the current engine performance is acceptable and satisfactory to be used for aircraft propulsion education, a safer and more reliable testing arrangement is still needed. Considering

Item Type:Thesis (Masters)
Subjects:T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL500-778 Aeronautics. Aeronautical engineering
ID Code:2666
Deposited By:Normajihan Abd. Rahman
Deposited On:23 Nov 2012 17:28
Last Modified:23 Nov 2012 17:28

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