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.

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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 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.
COMPARED THE TURBO ROCKET ENGINE WITH TURBO RAMJET ENGINE in airplane
Consider a cold air-standard Diesel cycle. Operating data at principal states in the cycle are given in the table below. The states are numbered as in Fig. 9.5 with p1 = 100 kPa, T1 = 340 K, and T3 = 4850.3 K, r = 12 and rc = 2. For n = 1.3, cv = 0.718 kJ/(kg-K), and cp = 1.005 kJ/(kg-K), determine p2 in kPa. (A) 3380.02 B) 4431.27 (C) 2528.92 D) 3675.83
Consider a cold air-standard Diesel cycle. Operating data at principal states in the cycle are given in the table below. The states are numbered as in Fig. 9.5 with p1 = 100 kPa, T1 = 340 K, and T3 = 4850.3 K, r = 12 and rc = 2. For n = 1.3, cv = 0.718 kJ/(kg-K), and cp = 1.005 kJ/(kg-K), determine p2 in kPa.
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.
Consider a cold air-standard Diesel cycle. Operating data at principal states in the cycle are given in the table below. The states are numbered as in Fig. 9.5 with p1 = 100 kPa, T1 = 340 K, and T3 = 4850.3 K, r = 12 and rc = 2. For n = 1.3, cv = 0.718 kJ/(kg-K), and cp = 1.005 kJ/(kg-K), determine the heat transfer during heat addition process per unit mass in kJ/kg. A) 3865.1 B) 4104.58 C) 3838.71 (D) 4154.44
In Otto Cycle, air at 18oC is first compressed to one-ninth of its original volume. If the heat input to the cycle is 460 KJ/Kg of air, determine a. The temperature of the remaining points in the cycle. b. The ratio of the maximum and minimum pressure in the cycle.
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…
Explain briefly by writing the thermal equilibrium equation in engines.
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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