Qn:Air enters a turbojet engine at 11.8 lbf/in.2, 430°R, and an inlet velocity of 620 miles/h...

Question

Qn:Air enters a turbojet engine at 11.8 lbf/in.2, 430°R, and an inlet velocity of 620 miles/h XXXXXXXXXXft/s). The pressure ratio across the compressor is 8. The turbine inlet temperature is 2150°R and the pressure at the nozzle exit is 11.8 lbf/in.2 determine the velocity at the exit to the nozzle, the mass and energy rate balances for a control volume enclosing this component reduce at steady state
	
Document Preview: Qn:Air enters a turbojet engine at 11.8 lbf/in.2, 430°R, and an inlet velocity of 620 miles/h XXXXXXXXXXft/s). The pressure ratio across the compressor is 8. The turbine inlet temperature is 2150°R and the pressure at the nozzle exit is 11.8 lbf/in.2  determine the velocity at the exit to the nozzle, the mass and energy rate balances for a control volume enclosing this component reduce at steady state

David · Accepted Answer

Qn:Air enters a turbojet engine at 11.8 lbf/in.2, 430°R, and an inlet velocity of 620 miles/h (909.3 
ft/s). The pressure ratio across the compressor is 8. The turbine inlet temperature is 2150°R and the 
pressure at the nozzle exit is 11.8 lbf/in.2  determine the velocity at the exit to the nozzle, the mass 
and energy rate balances for a control volume enclosing this component reduce at steady state
Ans:The work developed by the turbine equals the compressor work input. The diffuser, compressor, 
turbine, and nozzle processes are isentropic, and there is no pressure drop for flow through the 
combustor.  
For operation at steady state, determine the velocity at the nozzle exit and the pressure at each 
principal state. Neglect kinetic energy at the exit of all components except the nozzle and neglect 
potential energy throughout.
Each component is analyzed as a control volume at steady state. The control volumes are shown 
on the sketch by dashed lines. 
 The diffuser, compressor, turbine, and nozzle processes are isentropic.

Qn:Air enters a turbojet engine at 11.8 lbf/in. 2 , 430°R, and an inlet velocity of 620 miles/h XXXXXXXXXXft/s). The pressure ratio across the compressor is 8. The turbine inlet temperature is 2150°R...

Solution

Answer To This Question Is Available To Download

Related Questions & Answers

Submit New Assignment