AME436-S08-PS6

AME436-S08-PS6 - AME 436 Problem Set#6 Assigned Due at 4:30...

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AME 436 Assigned: 4/18/08 Problem Set #6 Due: 4/25/08 at 4:30 pm in my office mailbox (OHE 430J) (fax to me at 213-740-8071 if you’re off campus) Problem #1 (from last year’s final exam) In an ideal τ λ -limited turbojet with afterburner how would the T-s diagram be affected if a) The compressor is irreversible, but all other components are still ideal b) A new turbine with a higher maximum allowable inlet temperature is used, thus τ λ increases (but the afterburner temperature limit τ λ , AB does not change.) c) There are pressure losses in both the main burner and the afterburner (all other components are still ideal) d) A new fuel with a larger heating value per unit mass is used Show your results on the T-s diagrams below. In some cases there may be no change to the cycle. Assume that the compressor pressure ratio is the same for all cycles. When useful, add statements like “this Δ T = that Δ T,” “this area = that area,” etc. Please make your modifications clear; cycles that look like random scribbles and have no explanations don’t get much credit! a) The compressor is irreversible, but all other components are still ideal.
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b) A new turbine with a higher maximum allowable inlet temperature is used, thus τ λ increases (but the afterburner temperature limit τ λ , AB does not change.) c) There are pressure losses in both the main burner and the afterburner (all other components are still ideal.) d) A new fuel with a larger heating value per unit mass is used.
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  • Spring '08
  • Ronney
  • Turbofan, turbine¬†inlet¬†temperature, inlet temperature, compressor pressure ratio, flight Mach number

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AME436-S08-PS6 - AME 436 Problem Set#6 Assigned Due at 4:30...

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