As shown in the figure below, air enters the diffuser of a jet engine operating at steady state at 18 kPa, T1 = 223 K and a velocity of 265 m/s, all data corresponding to high-altitude flight. The air flows adiabatically through the diffuser and achieves a temperature of 250 K at the diffuser exit. Diffuser, Compressor - Combustors -Turbine - Nozzle Pi = 18 kPa T V1 = 265 m/s T= 250 K Air Product in gases out 2 Using the ideal gas model for air, determine the velocity of the air at the diffuser exit, in m/s. V2 = i m/s

As shown in the figure below, air enters the diffuser of a jet engine operating at steady state at 18 kPa, T1 = 223 K and a velocity of 265 m/s, all data corresponding to high-altitude flight. The air flows adiabatically through the diffuser and achieves a temperature of 250 K at the diffuser exit. Diffuser, Compressor - Combustors -Turbine - Nozzle Pi = 18 kPa T V1 = 265 m/s T= 250 K Air Product in gases out 2 Using the ideal gas model for air, determine the velocity of the air at the diffuser exit, in m/s. V2 = i m/s

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

8Air enters the diffuser of a ramjet engine (schematic shown below) at 6 lbf/in.2, 420°R, with a velocity of 1800 ft/s, and decelerates essentially to zero velocity. After combustion, the gases reach a temperature of 2000°R before being discharged through the nozzle at 6 lbf/in.2 On the basis of an air-standard analysis, determine:(a) the pressure at the diffuser exit, in lbf/in.2(b) the velocity at the nozzle exit, in ft/s.Neglect kinetic energy except at the diffuser inlet and the nozzle exit. Assume combustion occurs at constant pressure and flow through the diffuser and nozzle is isentropic.
Air enters the diffuser of a ramjet engine (schematic shown below) at 6 lbf/in.2, 420°R, with a velocity of 1600 ft/s, and decelerates essentially to zero velocity. After combustion, the gases reach a temperature of 2200°R before being discharged through the nozzle at 6 lbf/in.2 On the basis of an air-standard analysis, determine:(a) the pressure at the diffuser exit, in lbf/in.2(b) the velocity at the nozzle exit, in ft/s.Neglect kinetic energy except at the diffuser inlet and the nozzle exit. Assume combustion occurs at constant pressure and flow through the diffuser and nozzle is isentropic.
Water is compressed adiabatically, but inefficiently, from p1 = 150 kPa and T1 = 160 ∘C to a pressureof p2 = 700 kPa. A throttle valve is connected to the outlet of the compressor and has a temperature reading atits outlet of T3 = 440 ∘C at atmospheric pressure (1 bar). If the compressor operates at steady state, stray heattransfer can be neglected, and the changes in kinetic and potential energy are negligible, determine the isentropicefficiency of the compressor, in percent.
Where necessary, assume air as an ideal gas and consider R = 287J/(kg.K), Cp = 1005 J/(kg.K), Cv = 718 J/(kg.K). A nozzle is a device that is used to increase the velocity of a fluid by varying the cross-sectional area. At the last section of a jet engine (Fig Q1.a, section 5), air with a mass flow rate of 50 kg/s at a pressure of 500 kPa and a temperature of 600 K enters a nozzle with an inlet cross-sectional area of 5 m2. The exit area of the nozzle is 20% of its inlet area. The air leaves the nozzle at a velocity of 300 m/s. The nozzle is not well-insulated and duringthis process, 5 kJ/kg heat is lost. (i) In analysing this nozzle using the 1st law of thermodynamics,the change in which type of energy is negligible? (ii) Determine the density and velocity of the air entering thenozzle. (iii) Calculate the density of the air as it leaves the nozzle.
8 A certain SSSF, adiabatic control volume with single inflow and outflow streams has mass-flow-rate, m(dot) = 7.5 kg/sec, and a specific entropy increase from inflow, to outflow, se-si= +1.6 kJ/(K * Kg). Determine dSnet / dt ( in kJ/(degrees Kelvin * sec)), which is the time-rate-of-change, net, of the entropy of the universe (control volume plus surroundings).
A steam turbine seems to operate at a mass flow rate of 1.5 kg / hr. Turbine inlet state P1 = 2 MPa, T1 = 400C and V1 = 60 m / s; the output state is P2 = 0.1 MPa, x2 = 0.97 and V2 = 150 m / s. Difference in height between turbine outlet 1 m. The heat loss from the turbine is given as 50 kW. a) Determine the production power from the turbine. b) Turbine power neglecting Kinetic and Potential energy changes calculation. Interpret these two results. c) Turbine spring and cross section areas, as well as steam pipe diameters calculation. d) If the ambient temperature is 27C, what is the entropy generation in the turbine?
Steam flows at steady state through a converging, insulated nozzle, 25 cm long and with an inlet diameter of 5 cm. At the nozzle entrance, the temperature and pressure are 325 °C and 700 kPa, and the velocity is 30 m/s. At the nozzle exit, the steam temperature and pressure are 240 °C and 350 kPa. Property values are: H1= 3112.5 kJ/kg, V1 = 388.61 cm3/g, H2 = 2945.7 kJ/kg, V2 = 667.75 cm3/g. What is the velocity of the steam at the nozzle exit and what is the exit diameter?
Q13: 15 kg of air per minute is delivered by a centrifugal compressor. The inlet and outlet conditions of air are / C * l = 10 m/s, pl = 1 bar, v1=0.5 m3/kg and C2= 1 80 m/s , p2=7 bar, v2=0.15 m3/kg . The increase in enthalpy of air passing through the compressor is 60 kg/kg , and heat loss to the surroundings is 720 kJ/min. Assuming that inlet and discharge lines are at the same level, find : (i) Motor power required to drive the compressor. (ii) Ratio of inlet to outlet pipe diameter
An ideal gas passes a diffuser. At the diffuser inlet, the temperature is T1 = 350.00 K, the pressure P1 = 100.00 kPa, the velocity V1 = 200.00 m/s, and the inlet area A1 = 0.30 m2. At the exit, the velocity is very small. The specific heat of the ideal gas at the constant pressure is cp = 1.0050 kJ/(kg·K). The gas constant is R = 0.2870 kPa·m3/(kg·K). Determine the enthalpy per unit mass at the inlet, h1__________(kJ/kg)
An ideal gas passes a diffuser. At the diffuser inlet, the temperature is T1 = 350.00 K, the pressure P1 = 100.00 kPa, the velocity V1 = 200.00 m/s, and the inlet area A1 = 0.30 m2. At the exit, the velocity is very small. The specific heat of the ideal gas at the constant pressure is cp = 1.0050 kJ/(kg·K). The gas constant is R = 0.2870 kPa·m3/(kg·K). Determine the enthalpy per unit mass at the exit, h2__________(kJ/kg)
Where necessary, assume air as an ideal gas and consider R = 287 J/(kg.K), Cp = 1005 J/(kg.K), Cv = 718 J/(kg.K). a) A nozzle is a device that is used to increase the velocity of a fluid by varying the cross-sectional area. At the last section of a jet engine (Fig Q1.a, section 5), air with a mass flow rate of 50 kg/s at a pressure of 500 kPa and a temperature of 600 K enters a nozzle with an inlet cross-sectional area of 5 m2. The exit area of the nozzle is 20% of its inlet area. The air leaves the nozzle at a velocity of 300 m/s. The nozzle is not well-insulated and during this process, 5 kJ/kg heat is lost.Figure Q1.a: Schematic of a Jet engine.(iii) Calculate the density of the air as it leaves the nozzle.
Where necessary, assume air as an ideal gas and consider R = 287 J/(kg.K), Cp = 1005 J/(kg.K), Cv = 718 J/(kg.K). a) A nozzle is a device that is used to increase the velocity of a fluid by varying the cross-sectional area. At the last section of a jet engine (Fig Q1.a, section 5), air with a mass flow rate of 50 kg/s at a pressure of 500 kPa and a temperature of 600 K enters a nozzle with an inlet cross-sectional area of 5 m2. The exit area of the nozzle is 20% of its inlet area. The air leaves the nozzle at a velocity of 300 m/s. The nozzle is not well-insulated and during this process, 5 kJ/kg heat is lost. Figure Q1.a: Schematic of a Jet engine.(ii) Determine the density and velocity of the air entering thenozzle.