ME 430 THERMO-SYSTEM ANALYSIS AND DESIGN 1) Air at (19+0.5*A) °C enters a turbojet engine at a rate of m, kg/s and at a velocity of (300+A) m/s (relative to the engine). Air is heated in the combustion chamber at a rate and it leaves the engine at (430+0.5*A) °C. Determine m, and the rate of additional heat for the thrust of 12000 F produced by this turbojet engine, choose the entire engine as your control volume. A = LAST DIGIT OF YOUR CLASS ID kJ/s

ME 430 THERMO-SYSTEM ANALYSIS AND DESIGN 1) Air at (19+0.5A) °C enters a turbojet engine at a rate of m, kg/s and at a velocity of (300+A) m/s (relative to the engine). Air is heated in the combustion chamber at a rate and it leaves the engine at (430+0.5A) °C. Determine m, and the rate of additional heat for the thrust of 12000 F produced by this turbojet engine, choose the entire engine as your control volume. A = LAST DIGIT OF YOUR CLASS ID kJ/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

10- Argon enters an isentropic turbine at 450°C and exits at 150°C. If the turbine power is requested as 0.5 MW, which of the following is the required mass flow rate? A) 0,867 kg/s B) 1,667 kg/s C) 8,013 kg/s D) 0,312 kg/s E) 3,203 kg/s
A turbojet aircraft is flying with a velocity of 280 m/s at an altitude of 9150 m, where the ambient conditions are 32 kPa and −32°C. The pressure ratio across the compressor is 12, and the temperature at the turbine inlet is 1100 K. Air enters the compressor at a rate of 50 kg/s, and the jet fuel has a heating value of 42,700 kJ/kg. Assuming ideal operation for all components and constant specific heats for air at room temperature, determine the velocity of the exhaust gases,
A turbine operates under steady flow conditions, receiving steam at the following state: pressure 1200 KPa, temperature 1880°C, enthalpy 2785 KJ/kg, speed 33.3 m/s and elevation 3 m. The steam leaves the turbine at the following pressure 20 KPa, enthalpy 2512 KJ/kg, speed 100 m/s and elevation 0 m. Heat is lost to the surroundings at the rate of 0.29 KJ/s. If the rate of steam flow through the turbine is 0.42 kg/s. Find: A. Potential Energy 1, KJ/kg. B. Potential Energy 2 in KJ/kg. C. Kinetic Energy 1 in KJ/kg. D. Kinetic Energy 2 in KJ/kg. E. Heat Energy in KJ/kg. F. Power Output in KW.
11Air gas expands isentropically through a converging nozzle from a large tank at 160 lbf/in2, 600°R, and discharges into a region at 50 lbf/in2. The exit flow area is 1 in2. For air, use Cp = 0.24 Btu/lb.R. a. Determine the pressure at the exit in lbf/in2 b. Determine the mass flow rate through the nozzle, in lb/s
Air enters the compressor of a regenerative gas-turbine engine at 310 K and 100 kPa, where it is compressed to 900 kPa and 650 K. The regenerator has an effectiveness of 80 percent, and the air enters the turbine at 1400 K. For a turbine efficiency of 90 percent, determine (a) the amount of heat transfer in the regenerator and (b) the thermal efficiency. Assume variable specific heats for air.
A turboprop engine consists of a diffuser, compressor, combustor, turbine, and nozzle. The turbine drives a propeller as well as the compressor, delivering a net power of 1 MW to the propeller. Air enters the diffuser at 8000 m altitude (Ta = 236K, pa = 36 kPa) with a velocity of 550 km/h, and decelerates essentially to zero velocity. The compressor pressure ratio is 5.3 and the compressor has an isentropic efficiency of 83%. The turbine inlet temperature is 1360 K, and its isentropic efficiency is 86%. The turbine exit pressure is 10 kPa higher than the ambient pressure at that altitude. Flow through the diffuser and nozzle is isentropic. Neglect kinetic energy except at the diffuser inlet and the nozzle exit. Using an air-standard analysis, determine: a) The mass and volumetric flow rates entering the diffuser, in kg/s and m3/s, respectively.b) The rate of heat addition to the combustor, in MW.c) The velocity at the nozzle exit, in m/s.
A turbojet aircraft is flying with a velocity of 280 m/s at an altitude of 9150 m, where the ambient conditions are 32 kPa and −32°C. The pressure ratio across the compressor is 12, and the temperature at the turbine inlet is 1100 K. Air enters the compressor at a rate of 50 kg/s, and the jet fuel has a heating value of 42,700 kJ/kg. Assuming ideal operation for all components and constant specific heats for air at room temperature, determine the rate of fuel consumption.
Air at a 800 kPa and 1300 K enters a turbine which has an isentropic efficiency of 90% with a mass ﬂow rate 6 kg/s. The outlet pressure is 100 kPa and assume that speciﬁc heats are constant and evaluated at 600 K. 1. How much power is produced in kW? Round your answer to the nearest whole number. 2. What is the outlet temperature in K? Round your answer to one decimal place.
A turbine operates under steady flow conditions, receiving steam at the following state: pressure 1200kPa, temperature 188℃, enthalpy 2785 KJ/kg, speed=33.3m/s and elevation of 3m . The steam leaves the turbine at the following state; pressure=20kPa, enthalpy 2512 kJ/kg. Speed 100m/s and elevation 0 m. Heat is lost to the surroundings at the rate of 0.29 kJ/s. If the rate of steam flow through a turbine is 0.42 kg/s, what is the power output of the turbine in kW?
Air with mass flow rate of 1 kg/s enters the first stage of a compressor at 100 kPa and 300 K and exit the second stage of the compressor at 2677 kPa. If the compressed air outgoing from the first stage of the compressor passes through an intercooler, then enters the second stage of the compressor at temperature 353 K. What is the indicated isothermal efficiency for the compressor assuming ideal compression process with polytropica index n = 1.3 for both stages, no pressure loss in the intercooler, and the pressure ratio across the first and the second stage of the compressor are equal?
A turbine, operating under steady-flow conditions, receives X1 kg of steam per hour (For X1 refer Table. 1). The steam enters the turbine at a velocity of 3000 m/min, an elevation of 5 m and a specific enthalpy of 2787 kJ/kg. It leaves the turbine at a velocity of 6000 m/min, an elevation of 1 m and a specific enthalpy of 2259 kJ/kg. Heat losses from the turbine to the surroundings amount to 16736 kJ/h. Determine the power output of the turbine.
Hot combustion gases enter the nozzle of a turbojet engine at 350 kPa, 1007 0C, and 95 m/s, and they exit at a pressure of 100 kPa. Assuming an isentropic efficiency of 95 percent and treating the combustion gases as air determine a- The exit velocity b- The exit temperature