Rocket engine combustion chamberLiquid hydrazine (N 2 H 4 ) at 25 degrees Celsius, 0.1 MPa pressure andoxygen gas (O 2 ) at 25 degrees Celsius, 0.1 MPa pressureare fed into a combustion chamber in the ratio of 0.5 kg/sec O 2 to 1 kg/sec hydrazine.The heat loss from the products to the chamber walls is 1000 kJ per kg hydrazine The heating value Q R of hydrazine is 19,400 kJ/kg of fuelAssume that only H 2 O, H 2 and N 2 can be in the products.Assume that the heat capacity cp of all species is the same and is equal to 6.0 kJ/(kg-K).Assume that there is a steady flow in and out of the combustion zone, but the gas velocityremains negligibly small in the combustion zone, so static and stagnation temperatures arethe sameIn the products, the number of moles of H 2 O is a, the number of moles of H 2 is b and thenumber of moles of N 2 is c. a) Compute a, b and c. b) Determine the temperature of the products of combustion, in Kelvin. Please show all work!!
Rocket engine combustion chamberLiquid hydrazine (N 2 H 4 ) at 25 degrees Celsius, 0.1 MPa pressure andoxygen gas (O 2 ) at 25 degrees Celsius, 0.1 MPa pressureare fed into a combustion chamber in the ratio of 0.5 kg/sec O 2 to 1 kg/sec hydrazine.The heat loss from the products to the chamber walls is 1000 kJ per kg hydrazine The heating value Q R of hydrazine is 19,400 kJ/kg of fuelAssume that only H 2 O, H 2 and N 2 can be in the products.Assume that the heat capacity cp of all species is the same and is equal to 6.0 kJ/(kg-K).Assume that there is a steady flow in and out of the combustion zone, but the gas velocityremains negligibly small in the combustion zone, so static and stagnation temperatures arethe sameIn the products, the number of moles of H 2 O is a, the number of moles of H 2 is b and thenumber of moles of N 2 is c. a) Compute a, b and c. b) Determine the temperature of the products of combustion, in Kelvin. Please show all work!!
General Chemistry - Standalone book (MindTap Course List)
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Chapter6: Thermochemisty
Section: Chapter Questions
Problem 6.141QP
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Question
Rocket engine combustion chamber
Liquid hydrazine (N 2 H 4 ) at 25 degrees Celsius, 0.1 MPa pressure and
oxygen gas (O 2 ) at 25 degrees Celsius, 0.1 MPa pressure
are fed into a combustion chamber in the ratio of 0.5 kg/sec O 2 to 1 kg/sec hydrazine.
The heat loss from the products to the chamber walls is 1000 kJ per kg hydrazine
Liquid hydrazine (N 2 H 4 ) at 25 degrees Celsius, 0.1 MPa pressure and
oxygen gas (O 2 ) at 25 degrees Celsius, 0.1 MPa pressure
are fed into a combustion chamber in the ratio of 0.5 kg/sec O 2 to 1 kg/sec hydrazine.
The heat loss from the products to the chamber walls is 1000 kJ per kg hydrazine
The heating value Q R of hydrazine is 19,400 kJ/kg of fuel
Assume that only H 2 O, H 2 and N 2 can be in the products.
Assume that the heat capacity cp of all species is the same and is equal to 6.0 kJ/(kg-K).
Assume that there is a steady flow in and out of the combustion zone, but the gas velocity
remains negligibly small in the combustion zone, so static and stagnation temperatures are
the same
In the products, the number of moles of H 2 O is a, the number of moles of H 2 is b and the
number of moles of N 2 is c.
Assume that only H 2 O, H 2 and N 2 can be in the products.
Assume that the heat capacity cp of all species is the same and is equal to 6.0 kJ/(kg-K).
Assume that there is a steady flow in and out of the combustion zone, but the gas velocity
remains negligibly small in the combustion zone, so static and stagnation temperatures are
the same
In the products, the number of moles of H 2 O is a, the number of moles of H 2 is b and the
number of moles of N 2 is c.
a) Compute a, b and c.
b) Determine the temperature of the products of combustion, in Kelvin.
Please show all work!!
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