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Calculate the isentropic efficiency of a real, level 4-technology diffuser of an engine mounted in the airframe of a subsonic aircraft operating at Mach 0.8. Calculate the isentropic efficien...
Supersonic aircraft develop shock waves at the engine inlet when it flies supersonically. Consider the two...
Supersonic aircraft develop shock waves at the engine inlet when it flies supersonically. Consider the two types of engine inlets described as follows and calculate the total pressure recovery ratio for each engine inlet design when the aircraft flies at Mach 2.5. Take the specific heat ratio y to be 1.4. (a) A three-shock system (two oblique + one normal, external compression inlet) as shown in Fig. 1 Please note that the two blue arrows are not part of the...
ta Vew Wiadcw Helpr Home Tocls 101 2019.0.Cot QUESTION 9 In a jet engine rotor the high pressure axial compressor ro...
ta Vew Wiadcw Helpr Home Tocls 101 2019.0.Cot QUESTION 9 In a jet engine rotor the high pressure axial compressor rotates at a speed of 15000 rpm. The overall stagnation pressure ratio due to compression is 10.1, it was recorded that the air flows at a rate of 16 kg/s. The stagnation properties at the inlet are 215 kPa and 460K. The poly-tropic efficiency of the compressor is 90%. Assume the mean radius of the compressor is constant and equal...
Problem # 1 (60pts) a) 45pts A real engine with single-stage turbine and compressor operates at M...
Problem # 1 (60pts) a) 45pts A real engine with single-stage turbine and compressor operates at Mach 0.8 at 10km of altitude (pe 26kPa. To 223K). Calculate the power per unit flow rate of the turbine Gie W knowing the compressor pressure ratio T 10. Assume level 4 technology efficiencies, and that the air across the compressor is calorically perfect. b) 15pts Without actually calculating it, show all the equations that you would use to retrieve the incoming flow rate...
2. An aircraft with a single turbojet engine (with an inlet area of 1 m2) is...
2. An aircraft with a single turbojet engine (with an inlet area of 1 m2) is flying at cruising condition with a flight Mach number of 0.7. The ambient temperature and pressure are 250 K and 100 kPa, respectively. The engine compressor pressure ratio is 12, and the turbine inlet temperature is 1200 K. Assume all mechanical components are operating at isentropic condition and the specific heat can be considered a constant (throughout the entire engine) of 1 kJ/(kg K)....
Calculate the total temperature downstream of a real, level-4 technology nozzle knowing that T9-1,000 K, V9-1,250m/s and с/,,-1,300J/(kgK) Calculate the total temperature downstream of a real...
Calculate the total temperature downstream of a real, level-4 technology nozzle knowing that T9-1,000 K, V9-1,250m/s and с/,,-1,300J/(kgK)
Calculate the total temperature downstream of a real, level-4 technology nozzle knowing that T9-1,000 K, V9-1,250m/s and с/,,-1,300J/(kgK)
2. Two alternators A and B are operating in parallel to supply power to a load 1000 kVA at 0.8 pf laggine alternator A contributes 500 KVA at 0.6 of ageing calculate the real power and power factor o...
2. Two alternators A and B are operating in parallel to supply power to a load 1000 kVA at 0.8 pf laggine alternator A contributes 500 KVA at 0.6 of ageing calculate the real power and power factor of & iS points) 3. A 440 V, 4-pole, 60 Ht, 3-phase wye-connected induction motor runs at 1700 rpm during the normal operation. The motor has the following data; (20 polets X, 1.2 ohms 0.89 ohms X -0.56 ohms Ra 025 ohmg...
Supersonic aircraft develop shock waves at the engine inlet when it flies supersonically. Consider the two types of engine inlets described as follows and calculate the total pressure recovery ratio for each engine inlet design when the aircraft flies at Mach 2.5. Take the specific heat ratio y to be 1.4. (a) A three-shock system (two oblique + one normal, external compression inlet) as shown in Fig. 1 Please note that the two blue arrows are not part of the...
ta Vew Wiadcw Helpr Home Tocls 101 2019.0.Cot QUESTION 9 In a jet engine rotor the high pressure axial compressor rotates at a speed of 15000 rpm. The overall stagnation pressure ratio due to compression is 10.1, it was recorded that the air flows at a rate of 16 kg/s. The stagnation properties at the inlet are 215 kPa and 460K. The poly-tropic efficiency of the compressor is 90%. Assume the mean radius of the compressor is constant and equal...
Problem # 1 (60pts) a) 45pts A real engine with single-stage turbine and compressor operates at Mach 0.8 at 10km of altitude (pe 26kPa. To 223K). Calculate the power per unit flow rate of the turbine Gie W knowing the compressor pressure ratio T 10. Assume level 4 technology efficiencies, and that the air across the compressor is calorically perfect. b) 15pts Without actually calculating it, show all the equations that you would use to retrieve the incoming flow rate...
2. An aircraft with a single turbojet engine (with an inlet area of 1 m2) is flying at cruising condition with a flight Mach number of 0.7. The ambient temperature and pressure are 250 K and 100 kPa, respectively. The engine compressor pressure ratio is 12, and the turbine inlet temperature is 1200 K. Assume all mechanical components are operating at isentropic condition and the specific heat can be considered a constant (throughout the entire engine) of 1 kJ/(kg K)....
Calculate the total temperature downstream of a real, level-4 technology nozzle knowing that T9-1,000 K, V9-1,250m/s and с/,,-1,300J/(kgK)
Calculate the total temperature downstream of a real, level-4 technology nozzle knowing that T9-1,000 K, V9-1,250m/s and с/,,-1,300J/(kgK)
2. Two alternators A and B are operating in parallel to supply power to a load 1000 kVA at 0.8 pf laggine alternator A contributes 500 KVA at 0.6 of ageing calculate the real power and power factor of & iS points) 3. A 440 V, 4-pole, 60 Ht, 3-phase wye-connected induction motor runs at 1700 rpm during the normal operation. The motor has the following data; (20 polets X, 1.2 ohms 0.89 ohms X -0.56 ohms Ra 025 ohmg...
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