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Engine Performance

Project Description & Objectives

  • Used  type of code called Numerical Propulsion System Simulation (coded almost entirely in C++) to model and simulat various elements of propulsion systems

  • This code allows for building of an engine component by component (for example: diffuser - compressor - combustor - turbine - afterburner - nozzle)

  • In the case ran in NPSS to the right, the solver first runs a "design point" case for ideal separate flow turbofan engine flight thrust, altitude, and conditions

  • Then, engine points may be ran at difference diffuser inlet (altitude) and performance (FAR) inputs and the solver will match turbine output power to compressor input power

Accomplishments & Work Completed

  • See paper on the right for example of outputs from successfully executed code

  • Throttle hooks and operating lines ran for SFTF configuration

    • Plotting engine performance (thrust specific fuel consumption and combustor outlet temperature) based on percentage of maximum thrust at nominal operating inlet conditions​

    • Operating lines plotted over nominal engine conditions (pressure ratio vs corrected flow)

  • Entire engine deck (engine performance at off-nominal conditions) calculated:

    • Mach number sweep

    • Altitude sweep

    • Maximum thrust percentage sweep

    • Ram drag, fuel flow, and TSFC read as outputs

  • Finally, a relationship was established between TSFC and net thrust/mach number:

    • Fuel consumption increases at a higher rate as mach number increases and net thrust decreases (maintaining constant altitude)​

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