Ramjet, Turbojet and Turbofan Summary

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Presentation transcript:

Ramjet, Turbojet and Turbofan Summary MAE 5350: Gas Turbines Ramjet, Turbojet and Turbofan Summary Mechanical and Aerospace Engineering Department Florida Institute of Technology D. R. Kirk

RAMJETS Cycle analysis employing general form of mass, momentum and energy Energy (1st Law) balance across burner Thrust performance depends solely on total temperature rise across burner Relies completely on “ram” compression of air (slowing down high speed flow) Ramjet develops no static thrust

TURBOJET SUMMARY Cycle analysis employing general form of mass, momentum and energy Turbine power = compressor power How do we tie in fuel flow, fuel energy? Energy (1st Law) balance across burner

TURBOJET TRENDS: IN-CLASS EXAMPLE

TURBOJET TRENDS: IN-CLASS EXAMPLE (SEE INLET SLIDES FOR MORE DETAILS)

Tt4 = 1600 K, pc = 25, T0 = 220 K

Tt4 = 1400 K, T0 = 220 K, M0 = 0.85 and 1.2

Tt4 = 1400 K and 1800 K, T0 = 220 K, M0 = 0.85

TURBOFAN SUMMARY Two streams: Core and Fan Flow Turbine power = compressor + fan power Exhaust streams have same velocity: U6=U8 Maximum power, tc selected to maximize tf

TURBOFAN TRENDS: IN-CLASS EXAMPLE

TURBOFAN TRENDS: IN-CLASS EXAMPLE Improvement over turbojet: 4 – 2.4 → 66% at Mach 1 8 – 3.3 → 142% at Mach 0

TURBOFAN TRENDS: IN-CLASS EXAMPLE