ANALISIS PERFORMANCE TURBOSHAFT ENGINE T700-
GE-700 PADA HELICOPTER SIKORSKY UH-60A BLACK
HAWK DENGAN VARIASI KETINGGIAN
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
Yudhistira, Maza
Subject
T Technology (General)
Datestamp
2024-07-19 08:28:07
Abstract :
The ability to flights an aircraft can be determined by the performance of the aircraft engine and the aircraft's flights conditions. This study aims to determine the effect of altitude on the performance of the T700-GE-700 turboshaft engine used in the Sikorsky UH-60A black hawk helicopter. By calculating the value of fuel air ratio, specific thrust, specific fuel consumption, thermal efficiency, propulsive efficiency and overall efficiency as well as calculating the value of induced power during hover conditions. This research was conducted using four flights altitude, is 1000 ft, 2000 ft, 3000 ft, 4000 ft 5000 ft,, 6000 ft,7000 ft and 8000 ft. Before know the values, some input parameter data is needed. And to find out the value of fuel air ratio, specific thrust, specific fuel consumption, thermal efficiency, propulsive efficiency and overall efficiency using parametric cycle analysis and engine performance analysis methods, while to determine the value of induced power uses the equations contained in the momentum theory. The results obtained from this study are that altitude is very influential on the performance of an engine where the value of fuel air ratio, specific thrust, thermal efficiency, propulsive efficiency increases with the increase in flying altitude. This is due to the influence of the value of temperature, air density and air pressure at each altitude, but the specific fuel consumption value has decreased because the size of the specific fuel consumption value is determined by the value of the fuel air ratio and the value of specific thrust. For the value of induced power, the actual induced power value is greater than the ideal induced power it is due to the influence of the drag value.
The ability to flights an aircraft can be determined by the performance of the aircraft engine and the aircraft's flights conditions. This study aims to determine the effect of altitude on the performance of the T700-GE-700 turboshaft engine used in the Sikorsky UH-60A black hawk helicopter. By calculating the value of fuel air ratio, specific thrust, specific fuel consumption, thermal efficiency, propulsive efficiency and overall efficiency as well as calculating the value of induced power during hover conditions. This research was conducted using four flights altitude, is 1000 ft, 2000 ft, 3000 ft, 4000 ft 5000 ft,, 6000 ft,7000 ft and 8000 ft. Before know the values, some input parameter data is needed. And to find out the value of fuel air ratio, specific thrust, specific fuel consumption, thermal efficiency, propulsive efficiency and overall efficiency using parametric cycle analysis and engine performance analysis methods, while to determine the value of induced power uses the equations contained in the momentum theory. The results obtained from this study are that altitude is very influential on the performance of an engine where the value of fuel air ratio, specific thrust, thermal efficiency, propulsive efficiency increases with the increase in flying altitude. This is due to the influence of the value of temperature, air density and air pressure at each altitude, but the specific fuel consumption value has decreased because the size of the specific fuel consumption value is determined by the value of the fuel air ratio and the value of specific thrust. For the value of induced power, the actual induced power value is greater than the ideal induced power it is due to the influence of the drag value.
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