Thermodynamics - Steady State Nozzle, find area of inlet/exit

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SUMMARY

The discussion focuses on calculating the inlet and exit areas of a nozzle in a jet engine, given specific conditions: inlet temperature at 1000 K, pressure at 200 kPa, and velocity at 40 m/s, with an exit velocity of 500 m/s and pressure at 90 kPa. The exit temperature has been determined to be 890 K. The continuity equation is emphasized, indicating that mass flow rates at the inlet and exit must be equal, allowing for the calculation of area ratios between the inlet and exit. The assumptions include a closed system, steady state, and negligible work and heat transfer.

PREREQUISITES
  • Understanding of thermodynamics principles, specifically the first law of thermodynamics.
  • Familiarity with the continuity equation in fluid dynamics.
  • Knowledge of mass flow rate calculations in compressible flow.
  • Basic understanding of nozzle performance in jet engines.
NEXT STEPS
  • Study the derivation and application of the continuity equation in fluid dynamics.
  • Learn about the Bernoulli equation and its relevance to nozzle flow analysis.
  • Explore the concept of isentropic flow and its implications in nozzle design.
  • Investigate the effects of varying inlet conditions on nozzle performance metrics.
USEFUL FOR

Aerospace engineers, mechanical engineers, and students studying thermodynamics or fluid mechanics who are involved in jet engine design and analysis.

leafjerky
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Homework Statement


In a jet engine, a flow of air at 1000 K, 200 kPa, and 40 m/s enters a nozzle, where the air exits at 500 m/s and 90 kPa. What is the exit temperature, inlet area, and exit area, assuming no heat loss?

Homework Equations


min = mout = m
where m = mass air flow
dE/dt cv = Qcv - Wcv + Σmin(h+ (Vin/2)2 + gz) - Σmout(h+ (Vout/2)2 + gz)

exit area:
m = ρAV
where m = mass air flow, ρ = density, A = area, V = velocity

The Attempt at a Solution


I've already solved for the exit temperature to be 890 K. I just need to know how to find the exit/inlet areas.
 
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leafjerky said:

Homework Statement


In a jet engine, a flow of air at 1000 K, 200 kPa, and 40 m/s enters a nozzle, where the air exits at 500 m/s and 90 kPa. What is the exit temperature, inlet area, and exit area, assuming no heat loss?

Homework Equations


min = mout = m
where m = mass air flow
dE/dt cv = Qcv - Wcv + Σmin(h+ (Vin/2)2 + gz) - Σmout(h+ (Vout/2)2 + gz)

exit area:
m = ρAV
where m = mass air flow, ρ = density, A = area, V = velocity

The Attempt at a Solution


I've already solved for the exit temperature to be 890 K. I just need to know how to find the exit/inlet areas.
If there is no mass addition between the inlet and the exit, then doesn't continuity apply?

I don't know if you will be able to find the individual areas, but you should be able to calculate an area ratio between the inlet and exit.
 
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SteamKing said:
If there is no mass addition between the inlet and the exit, then doesn't continuity apply?

I don't know if you will be able to find the individual areas, but you should be able to calculate an area ratio between the inlet and exit.

In our problems with nozzles, I believe we are assuming the following:
  • closed system
  • steady state (de/dt = 0)
  • W = 0
  • Q = 0
  • PE = 0
I have emailed my teacher regarding the problem with the areas. I figured she must have left m out on accident. I just wanted to come on here and make sure. Thanks for your help as always SteamKing
 

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