Which of the following will aid in the selection of smaller combustion chamber volume during its design?

Low chamber pressure

Slightly reactive propellants

Injectors with moderate mixing

Possibility for complete combustion

Correct Answer : Possibility for complete combustion

Explanation : If there are means of achieving complete combustion, then the size of the combustion chamber may be reduced. Other than that, using highly reactive propellants (with adequate safety measures), having high chamber pressure and using injectors with good mixing will also act as factors for the selection of a smaller combustion chamber.

Recently Updated in Rocket Propulsion Questions

Determine the nozzle throat area for a rocket engine producing a total thrust of 10 kN, chamber pressure of 5.2 MPa and thrust coefficient of 1.9

10.12 cm²

11.20 cm²

12.10 cm²

21.10 cm²

Correct Answer : Option (A) : 10.12 cm²

Explaination : Nozzle throat area A_t = F/P₁C_F, where P₁ is the chamber pressure, C_F is the thrust coefficient and F is the total thrust provided by the rocket engine.
Then A_t = 10000/(5.2 x 10⁶ x 1.9)
= 10.12 cm².

The pressure drop across injector is usually set between _________ of the chamber pressure.

50 and 70%

45 and 65%

30 and 45%

15 and 25%

Correct Answer : Option (D) : 15 and 25%

Explaination : The pressure drop across the injector is set between 15 and 25% of the chamber pressure. This is done partly for obtaining high velocities of propellant injection. High velocities will help in easy atomization and droplet breakup which in turn helps in complete combustion.

Calculate the flow rate of LOX to the combustion chamber in a LOX-H2 rocket engine if the total propellant flow rate is 17 kg/s and mixture ratio is 3.2.

12.95 kg/s

13.67 kg/s

15.92 kg/s

17.81 kg/s

Correct Answer : Option (A) : 12.95 kg/s

Explaination : m?_o = m?_r/(r+1)
So m?_o = 17*3.2/4.2 = 12.95 kg/s.