Mod-01 Lec-02 Air breathing Engines - Turbojet I

[@brunorondon5529]

Very good teacher! Congratulations!

[@vikashdubey1594]

Thanku naptel

[@sandeepsapkota500]

Awesome Easy to understand 👍✈️

[@benjin3385]

When we are drawing the real turbojet Ts diagram, why did we ended up in the same pressure line? It actually means P3'=P3. why so?

[@sci-fi9158]

Thanks sir very helpful...

[@PlacementsatIIT]

Why process inside combustor is a constant pressure process?

[@rajatmond]

A better question is, why does the constant-pressure approximation work? Of course the air inside the combustor is an open system and the real process is not constant-anything, but that doesn't help us much. So we need to approximate. We can throw away isothermal(and adiabatic) right off the bat. now it comes to isobaric vs isochoric. If you restrict the airflow, then it will be "more constant-volume than constant-pressure" and vice versa. And then you draw a p-V diagram of the stages and you find that the engine is more efficient if it is constant-pressure. So you reduce the load(by shortening the turbines) and make it resemble a constant-pressure process.

[@YadavSiddheshDileepaeb]

18:54---sir,but turbine efficincy is for gas powercycle is generally 25-40% ,you wrote it as 87%,m confused in it sir

[@rajmehta8170]

Is this content enough for gate aerospace preparation???

[@bhukya18]

Didn't explain properly at the diffuser part.