P_o = 101.325 kPaT_o = 288 K Problem 6. Air at standard temperature and pressure is drawn steadily from a large room through an isentropic-converging nozzle into a frictionless, constant area duct with an inlet at Section (1) and an outlet at Section (2)The flow in the duct is diabatic (912 = 500 kJ/kg). For maximum flowrate, calculate at Section (1) andSection (2) (a) stagnation temperature and stagnation pressure, (b) static temperature and static pressure, and(c) flow speed. (d) Sketch the T-s diagram from the large room to Section (2). (e) Briefly discuss what will happen ifyou try to add more thermal energy to the flow with fixed room conditions for the case where the mass flowrateis also fixed and for the case where mass flowrate can change.Problem 6. (a) 288 K, 101 kPa, 786 K, 84.8 kPa, (b) 283 K, 94.8 kPa, 655 K, 44.8 kPa, (c) 105 m/s, 513 m/s

Answered: Image /qna-images/answer/6d8833f9-29e7-467c-bf86-fd396c88b988.jpg

Answered: Problem 6. Air at standard temperature…

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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Dry saturated steam at a pressure of 8 bar enters a convergent divergent nozzle and leaves it at a pressure of 1.5 bar. If the flow is isentropic and if the corresponding expansion index is 1.135, Determine the ratio of crosssectional area at exit and throat for maximum discharge
How do I find reservoir pressure given the exit-to-throat area ratio of a supersonic nozzle and a Pitot tube measurement from the test section.
Q.4. Air is fed from a large reservoir, where the temperature and pressure are 280 K and 300 kPa respectively, through isentropic converging-diverging nozzle. The diameters of throat and exit are 0.1 m and 0.15 m respectively. If there is a shock at the exit of the nozzle, determine: 1. the pressure and temperature at the exit of the duct. 2. the mass flow rate. Assume f=0.002
Q.2. Air flows through a constant-area duct is connected to a reservoir at a temperature of 500°C and a pressure of 500 kPa by a converging nozzle, as shown in Figure. Heat is lost at the rate of 250 kJ /kg. Determine the exit pressure and Mach number and the mass flow rate for a back pressure of 0 kPa. q = 250 kJ/kg P. = 500 kPa T, = 500°C Po = 0 kPa D = 0.02m
QUESTION 3 A high-pressure axial compressor for a stagnation pressure ratio of 8.5. The mass flow rate of air through the compressor is 16 kg/s and the stagnation conditions at inlet are 200 kPa and 450 K. The polytropic efficiency is 91 %. jet engine rotates at 15,000 rpm with and overall (a) If the mean radius is 0.24 m and this is constant throughout the compressor, calculate the total-to-total isentropic efficiency of the compressor and show that, for the stage loading to be less than 0.4 in all stages, eight stages required. are (b) The compressor is designed with repeating stages and zero inlet swirl. If the inlet axial Mach number is 0.52, calculate the mean flow coefficient and sketch the velocity triangles for one stage. Show that the blade height at exit from the compressor is about 7.8 mm.
Q.2. Air flows through a constant-area duct is connected to a reservoir at a temperature of 500°C and a pressure of 500 kPa by a converging nozzle, as shown in Figure. Heat is lost at the rate of 250 kJ /kg. Determine the exit pressure and Mach number and the mass flow rate for a back pressure of 0 kPa. q= 250 kJ/kg P.= 500 kPa T; = 500°C p. = 0 kPa D=0.02m
Consider steady adiabatic airflow in a duct. At section B,the pressure is 600 kPa and the temperature is 177°C. Atsection D, the density is 1.13 kg/m3 and the temperature is156°C. (a) Find the entropy change, if any. (b) Which wayis the air flowing?
A blade pair in an axial flow compressor is being designed. The axial flow component of gas velocity is 174m/s. The engine diameter at the mean blade height is 0.73m and the blade height at the rotor inlet is 0.21m. The rotor's absolute inlet flow angle is 26 degrees. The stagnation conditions at the inlet to the blade pair are 298K and 130kN/m² Using Cp 1.005k/kg/K, R-0.287k/kg/K, and taking the ratio of specific heat capacities as 1.4, calculate the engine mass flow rate to the nearest kg/s
multi-stage high –pressure steam turbine is supplied with steam at a stagnation pressure of 7 MPa and a stagnation temperature of 5000C. The corresponding specific enthalpy is 3410kJ.kg. The steam exhaust from the turbine at a stagnation pressure of 0.7 MPa abs., the steam having been in a super-heated condition throughout the expansion. It can be assumed that the steam behaves like a perfect gas over the range of the expansion and that ᵞ = 1.3. Given that the turbine flow process has a small-stage efficiency of 0.82, determine (1) the temperature and specific volume at the end of the expansion; (2) the re-heat factor. The specific volume of superheated steam is represented by pv=0.231(h-1943), where “p” is in kPa, v is in m3/kg and “h” is in kJ/kg.
Q.2. Air flows through a constant-area duct is connected to a reservoir at a temperature of 500°C and a pressure of 500 kPa by a converging nozzle, as shown in Figure. Heat is lost at the rate of 250 kJ /kg. Determine the exit pressure and Mach number and the mass flow rate for a back pressure of 0 kPa. q = 250 kJ/kg Pr = 500 kPa Tr = 500°C Po = 0 kPa D= 0.02m
An axial-flow compressor is to compress air from 27°C and 1 atm to 5 atm. The mean blade speed is 225 m/s and the stage loading coefficient is 0.4 for all the stages. If the stage efficiency is estimated to be 91%, how many stages are needed? (Taking Cp=1.005 kJ/kg-K and y=1.4) Answer: 10
Can you do part c please

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