ME300Lecture43

ME300Lecture43 - Lecture 43: Aircraft Propulsion Turbojet...

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43.1 Lecture 43: Aircraft Propulsion Turbojet Engine: fuel in y 1 2 3 4 5 Diffuser Compressor Combustor Turbine Nozzle air in exhaust gases
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43.2 Continue Turbojet Engine Ideal Cycle: s T Processes: y 1: decelerate air and increase pressure and temperature 1 2: compression 2 3: constant pressure heat addition 3 4: expansion, i.e., work production to drive compressor and other auxiliary devices only 1 2: accelerate air and decrease pressure and temperature, i.e., develop thrust 3 w C,s w T,s = w C,s 1 s 2 s 4 s 5 s w y
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43.3 Continue Turbojet Engine Relationship to stationary gas turbine: » Higher pressure ratios: p R = 10:1 up to 25:1 » No shaft work output (except for auxiliary equipment or turboprop engines, where turbine drives propeller) » Exhaust gases do not expand back to ambient pressure at turbine outlet (final expansion occurs in nozzle) » Diffuser in front of compressor increases pressure and decreases kinetic energy (ram effect)
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43.4 Continue Turbojet Engine Overall Performance: Assumptions : - neglect mass of fuel (single inlet, single outlet) - steady-state, steady flow - PE = 0 CV Air in .
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ME300Lecture43 - Lecture 43: Aircraft Propulsion Turbojet...

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