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on a streamline. What is the average acceleration over the distance? 2. Exhaust gases of specific...
Combustion Nozdc Exhaust Fud Exit - V - Velocity m- mass flow rate p- pressure Throat...
Combustion Nozdc Exhaust Fud Exit - V - Velocity m- mass flow rate p- pressure Throat 2.4 kg/s of liquid hydrogen and 24 kg/s of liquid oxygen enter a rocket engine where they are supposed to combust. A large leak in the combustion chamber allows 13 kg/s of the mixture to escape prior to combustion. (Assume that the leak is composed of the same proportion of Hz and Oz as flow into the engine.) The remaining gases combust, and the...
An oil engine develops 300 kW and the specific fuel consumption is 0.21 kg/kWh. The exhaust...
An oil engine develops 300 kW and the specific fuel consumption is 0.21 kg/kWh. The exhaust from the engine is used in a tubular water heater, flowing through 25 mm diameter tubes, entering with a velocity of 12 m/s, at 340 °C and leaving at 90 °C. The water enters the heater at 10 °C and leaves at 90 °C, flowing in counter-flow to the hot gases. The air-fuel ratio of the engine is 20, and the exhaust pressure is...
3. Diesel engine exhaust gases at 0.3 MPa pressure and 800 K pass through a nozzle, where the nozzle coefficient (G) is 0.98, and expand to a pressure of 0.12 MPa. The hot gases enter to a simple...
3. Diesel engine exhaust gases at 0.3 MPa pressure and 800 K pass through a nozzle, where the nozzle coefficient (G) is 0.98, and expand to a pressure of 0.12 MPa. The hot gases enter to a simple impulse turbine of the turbocharger unit with diameter 0.4 m, nozzle angle 12° and blade coefficient (o) of 0.99. Find: a. Ideal rate of rotation of turbine, in rpm b. The velocity of air leaving the turbine, assuming a symmetric bl c....
3. Diesel engine exhaust gases at 0.3 MPa pressure and 800 K pass through a nozzle, where the nozzle (Cn) is 0.98, and expand to a pressure of 0.12 MPa. The hot gases enter to a simple impulse tu...
3. Diesel engine exhaust gases at 0.3 MPa pressure and 800 K pass through a nozzle, where the nozzle (Cn) is 0.98, and expand to a pressure of 0.12 MPa. The hot gases enter to a simple impulse tu turbocharger unit with diameter 0.4 m, nozzle angle 120 and blade coefficient (cs) of 0.99. Find a. Ideal rate of rotation of turbine, in rpm b. The velocity of air leaving the turbine, assuming a symmetric blade c. Diagram efficiency d....
2. An aircraft with a single turbojet engine (with an inlet area of 1 m2) is...
2. An aircraft with a single turbojet engine (with an inlet area of 1 m2) is flying at cruising condition with a flight Mach number of 0.7. The ambient temperature and pressure are 250 K and 100 kPa, respectively. The engine compressor pressure ratio is 12, and the turbine inlet temperature is 1200 K. Assume all mechanical components are operating at isentropic condition and the specific heat can be considered a constant (throughout the entire engine) of 1 kJ/(kg K)....
Consider the flow through a rocket engine nozzle. In the combustion chamber, the gas which results...
Consider the flow through a rocket engine nozzle. In the combustion chamber, the gas which results from the combustion of the rocket fuel and oxidizer is at a pressure and temperature of 15 atm and 2500K, respectively; the molecular weight and specific heat at constant pressure of the combustion gas are 12 kg/kmol and 4157 J/kg · K, respectively. Assume that the gas flow through the nozzle is an isentropic expansion of calorically perfect gas, with a temperature of 1350K...
A small workboat is fitted with a diesel engine that develops its maximum power of 300...
A small workboat is fitted with a diesel engine that develops its maximum power of 300 kW with a corresponding specific fuel consumption of 0.21 kg/kW h. At maximum power, the air-fuel ratio of the engine is 20 and the exhaust pressure is 1.01 bar. It is proposed to provide hot water for the vessel by using a shell and tube heat exchanger to extract waste heat from the engine exhaust gases. Calculate the: (i) tube length required. The following...
For all of the processes, you may assume the gases have the properties of pure air...
For all of the processes, you may assume the gases have the properties of pure air and are thermally and calorically perfect. For all processes except the exhaust nozzle, you may neglect kinetic and potential energy changes. Therefore, the static and stagnation properties are equal. 50 kg/s of air enters an adiabatic compressor at 1 atm and 300 K and compresses the air to 30 atm. The compressor has an adiabatic efficiency of 90%. The compressor adiabatic efficiency is W...
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How does combustion tenper e te extent ol Teattiny Problem #2 A 4.0 Liter six-cylinder four-stroke SI square engine (bore and stroke 9.47 cm) with a direct injection system with one injector per cylinder is designed to have a maximum speed of 7000 RPM at wide open throttle with a stoichiometric air-fuel ratio of 14.6. The injector nozzle diameter is 0.2 mm. There is one intake valve per cylinder and the valve lift equals one fourth the valve diameter. The...
1.6 The Space Shuttle Transportation System (SSTS) shown in Fig. E1.5 incorporates three space shuttle main...
1.6 The Space Shuttle Transportation System (SSTS) shown in Fig. E1.5 incorporates three space shuttle main engines (SSME, shown in Fig. E1.6) using liquid hydrogen (L.H2) as the fuel and LOX as the oxidizer in a ratio of 1:6. The heating value of LH2 is 51.600 Btu/lh (120 MJ/kg). The thrust produced by each engine in near-vacuum conditions of the upper atmosphere is 512,000 Ibs (2.28 MN) at a specific impulse of 454 s. The typical burn time for the...
Combustion Nozdc Exhaust Fud Exit - V - Velocity m- mass flow rate p- pressure Throat 2.4 kg/s of liquid hydrogen and 24 kg/s of liquid oxygen enter a rocket engine where they are supposed to combust. A large leak in the combustion chamber allows 13 kg/s of the mixture to escape prior to combustion. (Assume that the leak is composed of the same proportion of Hz and Oz as flow into the engine.) The remaining gases combust, and the...
An oil engine develops 300 kW and the specific fuel consumption is 0.21 kg/kWh. The exhaust from the engine is used in a tubular water heater, flowing through 25 mm diameter tubes, entering with a velocity of 12 m/s, at 340 °C and leaving at 90 °C. The water enters the heater at 10 °C and leaves at 90 °C, flowing in counter-flow to the hot gases. The air-fuel ratio of the engine is 20, and the exhaust pressure is...
3. Diesel engine exhaust gases at 0.3 MPa pressure and 800 K pass through a nozzle, where the nozzle coefficient (G) is 0.98, and expand to a pressure of 0.12 MPa. The hot gases enter to a simple impulse turbine of the turbocharger unit with diameter 0.4 m, nozzle angle 12° and blade coefficient (o) of 0.99. Find: a. Ideal rate of rotation of turbine, in rpm b. The velocity of air leaving the turbine, assuming a symmetric bl c....
3. Diesel engine exhaust gases at 0.3 MPa pressure and 800 K pass through a nozzle, where the nozzle (Cn) is 0.98, and expand to a pressure of 0.12 MPa. The hot gases enter to a simple impulse tu turbocharger unit with diameter 0.4 m, nozzle angle 120 and blade coefficient (cs) of 0.99. Find a. Ideal rate of rotation of turbine, in rpm b. The velocity of air leaving the turbine, assuming a symmetric blade c. Diagram efficiency d....
2. An aircraft with a single turbojet engine (with an inlet area of 1 m2) is flying at cruising condition with a flight Mach number of 0.7. The ambient temperature and pressure are 250 K and 100 kPa, respectively. The engine compressor pressure ratio is 12, and the turbine inlet temperature is 1200 K. Assume all mechanical components are operating at isentropic condition and the specific heat can be considered a constant (throughout the entire engine) of 1 kJ/(kg K)....
Consider the flow through a rocket engine nozzle. In the combustion chamber, the gas which results from the combustion of the rocket fuel and oxidizer is at a pressure and temperature of 15 atm and 2500K, respectively; the molecular weight and specific heat at constant pressure of the combustion gas are 12 kg/kmol and 4157 J/kg · K, respectively. Assume that the gas flow through the nozzle is an isentropic expansion of calorically perfect gas, with a temperature of 1350K...
For all of the processes, you may assume the gases have the properties of pure air and are thermally and calorically perfect. For all processes except the exhaust nozzle, you may neglect kinetic and potential energy changes. Therefore, the static and stagnation properties are equal. 50 kg/s of air enters an adiabatic compressor at 1 atm and 300 K and compresses the air to 30 atm. The compressor has an adiabatic efficiency of 90%. The compressor adiabatic efficiency is W...
How does combustion tenper e te extent ol Teattiny Problem #2 A 4.0 Liter six-cylinder four-stroke SI square engine (bore and stroke 9.47 cm) with a direct injection system with one injector per cylinder is designed to have a maximum speed of 7000 RPM at wide open throttle with a stoichiometric air-fuel ratio of 14.6. The injector nozzle diameter is 0.2 mm. There is one intake valve per cylinder and the valve lift equals one fourth the valve diameter. The...
1.6 The Space Shuttle Transportation System (SSTS) shown in Fig. E1.5 incorporates three space shuttle main engines (SSME, shown in Fig. E1.6) using liquid hydrogen (L.H2) as the fuel and LOX as the oxidizer in a ratio of 1:6. The heating value of LH2 is 51.600 Btu/lh (120 MJ/kg). The thrust produced by each engine in near-vacuum conditions of the upper atmosphere is 512,000 Ibs (2.28 MN) at a specific impulse of 454 s. The typical burn time for the...
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