An aircraft flies at 960 kmph. One of its(c)turbojet engines takes in 40 kg/s of airand expands the gases to the ambientpressure. The air-fuel ratio is 50 andthe lower calorific value of the fuel is43 MJ/kg. For maximum thrust powerdetermine (i) jet velocity, (ü) specificthrust and (üi) thrust power.

Answered: Image /qna-images/answer/a483e39b-1993-4369-b7e2-47a1033e24a1.jpg

Answered: An aircraft flies at 960 kmph. One of…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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The pressure and temperature at the beginning of compression of an air-standard Diesel cycle are 80 kPa and 300 K, respectively. At the end of the heat addition, the pressure is 6821 kPa and the temperature is 1950 K. Step 1 Determine the compression ratio. r = i Save for Later Attempts: 0 of 3 used Submit Answer Step 2 The parts of this question must be completed in order. This part will be available when you complete the part above. Ston 3
An air-standard Diesel cycle has a maximum temperature of 2000 K. At the beginning of compression, p₁ = 95 kPa and T₁ = 300 K. The mass of air is 12 g. For a compression ratio of 25, determine: (a) the net work of the cycle, in kJ. (b) the percent thermal efficiency. (c) the mean effective pressure, in kPa.
3The rate of heat addition to an ideal air-standard Brayton cycle is 1.0 x 107 Btu/h. The pressure ratio for the cycle is 12 and the minimum and maximum temperatures are 520°R and 2800°R, respectively.Determine:(a) the percent thermal efficiency of the cycle.(b) the mass flow rate of air, in lb/h.(c) the net power developed by the cycle, in hp.
Two ideal Brayton cycles (see Figure below) have the same inlet temperature and the same maximum temperature of the turbine inlet. Brayton Cycle A has a higher compression ratio than Cycle B. Which of the following statements is true about the cycles? Cycle A has a higher thermal efficiency and Cycle B has a higher work net for a given mass flow rate. Cycle B has a higher thermal efficiency and a higher work net for a given mass flow rate. Since the temperatures are the same the efficiencies and work net are also the same. Cycle A has a higher work net for a given mass flow rate and Cycle B has a higher thermal efficiency. Cycle A has a higher thermal efficiency and a higher work net for a given mass flow rate.
The state at the beginning of compression of an air-standard Diesel cycle is fixed by p₁ = 100 kPa and T₁ = 310 K. The compression ratio is 18 and the cutoff ratio is 1.9. Determine: (a) the maximum temperature, in K. (b) the pressure at the end of the expansion, in kPa. (c) the net work per unit mass of air, in kJ/kg. (d) the percent thermal efficiency.
Air enters the compressor of an ideal air-standard Brayton cycle at 100 kPa, 314 K, with a volumetric flow rate of 5 m3/s. The compressor pressure ratio is 9:1. The turbine inlet temperature is 1400 K. Take Specific heat at constant pressure and constant volume for air as 1.006 kJ/kg K and 0.717 kJ/kg K respectively. Calculate the compressor exit absolute temperature to one decimal place and place the correct unit. Use the cold air-standard assumption.
An ideal gas Diesel engine, that has an inlet temperature and pressure of 19 0C and 102 kPa respectively with a compression ratio of 23:1. The maximum cycle temperature is 1,237 0C. Take Specific heat at constant pressure and constant volume for air as 1.005 kJ/kg K and 0.717 kJ/kg K respectively. Calculate the specific heat received to one decimal place and include the correct SI unit.
10. The initial design of an IFR turbine is to be based upon Whitfield’s procedure for optimum efficiency. The turbine is to be supplied with 2.2 kg/s of air, a stagnation pressure of 250 kPa, a stagnation temperature of 800°C, and have an output power of 450 kW. At turbine exit the static pressure is 105 kPA. Assuming for air that γ ¼ 1.33 and R ¼ 287 J/kg K, determine the valueof Whitfield’s power ratio, S, and the total-to-static efficiency of the turbine.
A turboshaft engine comprising a gas generator and a free power turbine is selected to provide propulsive power for a helicopter. The helicopter is hovering in ISA conditions at an altitude of 4100 feet. The following data applies to this engine at this static max power operating point. Intake mass flow: 8.9 kg/s Compressor pressure ratio: 24.5 Compressor isentropic efficiency: 88% Mechanical efficiency: (HP & PT shaft) 99% Combustion chamber pressure loss Combustion chamber inlet pressure 4% Combustion efficiency 98.8% Combustion chamber exit temperature: 1585K Gas generator turbine isentropic efficiency: 92% Power turbine isentropic efficiency: 90% The effects of the intake and exhaust ducts may be ignored. It may be assumed that for: Air: Cp = 1.005 kJ/kg • K, y = 1.4, R = 0.287 kJ/kg • K Combustion gases: Cp = 1.148kJ/kg • K, y = 1.333, R = 0.287 kJ/kg • K A 6% direct bleed of air from the exit of the compressor is…
The rate of heat addition to an ideal air-standard Brayton cycle is 1.0 x 107 Btu/h. The pressure ratio for the cycle is 12 and the minimum and maximum temperatures are 520°R and 2800°R, respectively.Determine:(a) the percent thermal efficiency of the cycle.(b) the mass flow rate of air, in lb/h.(c) the net power developed by the cycle, in hp.
2. A four-cycle, 5.866 L engine consumes 19 kg/hr of fuel and 413 kg/hr of air while running under full load at 2,400 rev/min. The air temperature is 24.2°C,and the barometric pressure is 98.13 KPa. Calculate (a.) the air density, (b.) the theoretical air consumption rate, , and (c.) the volumetric efficiency
What are the main reasons for running jet engines at high temperatures? Select one or more: a. Increased fuel burn b. Greater thermal creep c. Increased efficiency d. Higher thrust e. Decreased noise

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