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- Consider a rocket engine burning hydrogen and oxygen. The total massflow of the propellant plus oxidizer into the combustion chamber is287.2 kg/s. The combustion chamber temperature is 3600 K. Assumethat the combustion chamber is a low-velocity reservoir for the rocketengine. If the area of the rocket nozzle throat is 0.2 m2, calculate thecombustion chamber (reservoir) pressure. Assume that the gas that flowsthrough the engine has a ratio of specific heats, γ = 1.2, and a molecularweight of 16.A ramjet drives a missile at V0=966m/s at an altitude of 33.5km (air density 0.01kg/m3 and T0=232K). If the missile inlet captures a stream tube of air A0=1,1m2 in area, the fuel-to-air ratio is 0,049, and the fuel heating value is 50MJ/kg. if the ramjet engine produces net thrust Fn= 8,9 kN , What is the useful power that the engine introduces to the missile?12- Combustion gases (k=1.33) enter a convergent nozzle at a stagnation temperature of 350 oC and a stagnation pressure of 430 kPa and are vented to the atmosphere at 20 oC, 100 kPa. Which of the following is the lowest pressure that will occur in the nozzle?
- A 5-feet diameter Chimney is designed to handle a flue gas produced in a steam power plant at a rate of 17 lb/s. The barometric pressure is 29.92-inch Hg. Outside air enters the combustion chamber at 90 F. The average temperature of the flue gas inside the Chimney is 572 F and its molecular weight is 30. Cv = 0.35, Rair = 53.342 ft-lb/lb-R. Calculate: a. The total draft, feet of air. b. The height of the Chimney, feetA combustion chamber consists of combustion pipes with a diameter of 15 cm. Compressed air enters the pipes at 550 K, 480 kPa and 80 m/S (Figure 3). A fuel with a thermal value (ID) of 42000 kJ/kg is injected into the air and burned in such a way that the mass air-fuel ratio (HY) is 40. Considering the combustion event as a heat transfer to the air, at the exit of the combustion chambera) temperature,b) pressure,c) find the speed and Mach Number values. Note : k=1.4, cp=1.005 kJ/kg.K, R=0.287 kJ/kg.KAt a particular stage of a reaction turbine the mean blade speed is 140 m/sec and the steam is at a pressure of 20 bar with temperature of 250° C. Fixed and moving blades at this stage have inlet angles 30° and exit angles 20°. The stage efficiency is 80%. Determine (1) Specific entholpy drop across the stage in kJ/kg. (i) Drum Dia and blade height if heigh is one-twelfth of the drum dia. and the steam flow is 120 kg/sec. (ii) The percentage increase in the relative velocity across the bladings as a result of pressure drop across the blading.
- A 5-feet diameter Chimney is designed to handle a flue gas produced in a steam power plant at a rate of 17 lb/s. The barometric pressure is 29.92-inch Hg. Outside air enters the combustion chamber at 90 F. The average temperature of the flue gas inside the Chimney is 572 F and its molecular weight is 30. Cv = 0.35, Rair = 53.342 ft-lb/lb-R. Calculate: 5. The total draft, feet of air. 6. The height of the Chimney, feetAn ideal nitrogen gas enters an adiabatic diffuser at 178 kPa, 280.15 oK and 275 m/s, and it leaves through a cross section of 1 m2 at 100 kPa and 84.2 oF calculate the inlet area in cm2, consider cv=0.7422 kJ/kgoK, R=0.2968 kJ/kgoK and the absolute pressuresA power plant is situated at an altitude having an ambient air at 96.53 kPa and 23.88°C. Flue gases at a rate of 5 kg/s enter the stack at 200°C and leaves at 160°C. Calculate the diameter of the exhaust stack in meters for a driving pressure of 0.20 kPa. Note: The actual velocity is 40% of the theoretical velocity.
- Air flows through a converging-diverging (c-d) nozzle. It is supplied from a large air reservoir in which the temperature is 377 K and the pressure is 190 kPa. The velocity and the cross-sectional area at the nozzle exit are 462 m/s and 0.0005 m^2, respectively. Find the followings: Mach number at exit is Area of the throat is The mass flow rate of air is The exit temperature is The exit pressure isA 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/sCombustion 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.