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Unit 2 Aircraft Propulsion

Unit 2 Aircraft Propulsion. J Singh / MS Deepa Aeronautical. Refresher. Mass Transfer Reviewed Working of a Gas Turbine Engine Thrust Equation for Turbojet, Turbofan, Turboprop, Ramjet Engine Quiz Tutorial posted on “aero2016” google group

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Unit 2 Aircraft Propulsion

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  1. Unit 2 Aircraft Propulsion J Singh / MS Deepa Aeronautical

  2. Refresher • Mass Transfer • Reviewed Working of a Gas Turbine Engine • Thrust Equation for Turbojet, Turbofan, Turboprop, Ramjet Engine • Quiz • Tutorial posted on “aero2016” google group • 8th August, All tutorials will be discussed in the class. Pl work out individually

  3. Ideal (Brayton Cycle) • Compression and Expansion are Reversible and Adiabatic • Change of KE of working fluid between inlet and outlet of each component is negligible • No pressure losses in the inlet, CC, exhaust ducting, ducting • Working fluid has the same composition throughout the cycle • Perfect gas with constant specific heats • Mass flow of gas is constant throughout the cycle • Heat transfer is complete, so that Temperature rise on cold side equals the temperature drop on hot side

  4. Performance of Gas Turbine Cycles • Forward speed and Altitude • Specific Work output and Cycle Efficiency depend only on Pressure Ratio and Max Cycle Temperature

  5. Refresher • Tutorial posted on “aero2016” google group • 8th August, All tutorials will be discussed in the class. Pl work out individually • Question papers (class in-charge) • Brayton Cycle: Efficiency & Specific Work output (depend only on…. and…..)

  6. Cycle Analysis • Heat Exchange • Reheat • Intercooled Numerical (V.Ganesan)

  7. Factors affecting Thrust • Velocity • Temperature • Altitude / Pressure Also refer class notes provided

  8. Thrust • Propelling Nozzle Outlet: • Area (Ae) = 0.2150 m² • Pressure (Pe) = 143.325 kPa • Pressure (P0) = 101.325 kPa (ISA) • Mass Flow (W2) = 70 kg/s • Velocity (Vj) = 590 m/s Calculate Thrust (kN) at Sea Level Static Condition.

  9. Thrust with Reheat • Afterburner Propelling Nozzle Outlet: • Area (Ae) = 0.2900m² • Pressure (Pe) = 136.325 kPa • Pressure (o) = 101.325 kPa • Mass Flow (W2) = 70 kg/s • Velocity (Vj) = 740 m/s Calculate Thrust (kN) at Sea Level Static Condition.

  10. Thrust Augmentation • There are occasions when maximum thrust from a basic gas turbine engine is inadequate, and some method of increasing the available thrust is required

  11. Afterburning / Reheat This is employed to boost the thrust at various altitudes thus increasing aircraft performance. This is limited to short periods only, such as combat or take-off, due to the increased fuel consumption.

  12. Water / Water-Methanol Injection This is employed to restore, or even boost, the thrust from a gas turbine operating from hot or high altitude airfields. This method is now normally limited to turboprop powered transport aircraft.

  13. Aircraft engine schemes (1) Turboprop with two stage centrifugal compressor Twin-spool turboprop with axial compressor

  14. Aircraft engine schemes (2) Single spool turbojet with axial compressor Turboshaft with twin-spool gas generator Twin-spool bypass

  15. Aircraft engine schemes (3) Triple spool turbofan (separate exhausts) Unducted (aft)fan or propfan

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