1 A jet propelled plane consuming air at a rate of 18.2 kg/sec is to fly at Mach. No. 0.6 at an altitude of 4500 meter. (P 0.55 bar, T 255° K). The diffuser which has a pressure coefficient 0.9, decreases the flow to a negligible velocity. The compressor pressure ratio is 5 and inaximum temperature in the combustion ehamber is 1273 K. After expansing in the turbine, the gases continue to expand in the nozzle to a pressure of 0.69 bar. The isentropic efficiency of compressor is 0.81 and of turbine 0.95 and of nozzle 0.915. The heating value of the fuel if 45870 kJ/kg. Assuming C, = 1.005 kJ/kg=K, C, = 1.147 kJ/kg-K, Y,ir = 1.4, Yu. 1.33. Calculate %3D %3D %3D

1 A jet propelled plane consuming air at a rate of 18.2 kg/sec is to fly at Mach. No. 0.6 at an altitude of 4500 meter. (P 0.55 bar, T 255° K). The diffuser which has a pressure coefficient 0.9, decreases the flow to a negligible velocity. The compressor pressure ratio is 5 and inaximum temperature in the combustion ehamber is 1273 K. After expansing in the turbine, the gases continue to expand in the nozzle to a pressure of 0.69 bar. The isentropic efficiency of compressor is 0.81 and of turbine 0.95 and of nozzle 0.915. The heating value of the fuel if 45870 kJ/kg. Assuming C, = 1.005 kJ/kg=K, C, = 1.147 kJ/kg-K, Y,ir = 1.4, Yu. 1.33. Calculate %3D %3D %3D

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

See similar textbooks

Similar questions

There are 5kg/s of CO2 (R=188.96kJ/kg-K, k=1.288) gas compressed polytropically with n=1.2 from 103kPa, 60C to 1200kPa. What is the change in Enthalpy? (kJ/s)
There are 5kg/s of CO2 (R=188.96kJ/kg-K, k=1.288) gas compressed polytropically with n=1.2 from 103kPa, 60C to 1200kPa. What is the Work (steady flow) done? (kW)
pls solve in less than 30 min.pls fast.
2.23 Determine pressures and temperatures at all points of a Diesel air standard cycle when the ambient conditions are 25 "C and 100 kPa. Displacement volume is 750% of the clearance volume. Thermal efficiency is 60%. Heat rejection starts at 850 °C.
Thermodynamics Instructions: Answer the problem. a) Estimate the enthalpy and quality (or temperature) of the exhaust. *show complete solutions and please write legibly. TY
Steam @ 500 C and 6 MPa expands in a turbine to 50 kPa and enthalpy of 2585, the turbine is not insulated and losses 120 to the surroundings which are at 19°C. What is the entropy generated (kJ/kg.K)? Select one: A. 0.9515 B. 0.7517 C. 1.0276 O D. 0.5406 X E. 0.8278
Air enters the compressor of an ideal air standard brayton cycle at 100 kPa, 300 K, with a volumetric flow rate of 5 cu.m/s. The compressor pressure ratio is 10. The turbine inlet temperature is 1400 K. Compute the (a) P, V, and T at each point of the cycle; (b) QA, QR in kW; (c) WC, WT in kW; (d) rp, TBW; (e) e; (f) mep.
Consider the extraction of energy from the tail gases from a nitric acid adsorption tower, such as that described in Chapter 4, Example 4.4. Gas composition, kmol/h: 0₂ N₂ NO NO₂ H₂O 371.5 10,014.7 21.9 Trace saturated at 250°C If the gases leave the tower at 6 atm, 25°C, and are expanded to, say, 1.5 atm, calculate the turbine exit gas temperatures without preheat, and if the gases are preheated to 400°C with the reactor off-gas. Also, estimate the power recovered from the preheated gases.
i need the answer quickly
Please solve asap!!!!!!??:;
Air enters the compressor of an ideal air-standard Brayton cycle at 80 kPa, 299 K, with a volumetric flow rate of 6.1 m3/s. The compressor pressure ratio is 7. The turbine inlet temperature is 1886 K. Adopting the cold air-standard assumption, calculate: the mass flow rate of air to 3 d.p. in SI unit and privide unit symbol. Take the gas constant as 289 J/kg.K
Combustion gases with k=1.35, Cp =1107 J/(kg.K) and R= 287 J/(kg.K) flow at stagnation pressure and stagnation temperature of 390kPa and 1150 K respectively, flow through a 90o IFR turbine to an exit static pressure of 100 kPa. The total to static efficiency is 80% and the flow leaves the stator choked (Mach Number=1). The relative velocity at the inlet to the rotor is radial and the flow leaves the turbine without a swirl. Find (a) the work delivered per unit flow rate, (b) the impeller tip velocity and (c) the flow angle at the inlet to the rotor.