AeroEngineS

Aircraft Engine Performance at Design Point

• Subsonic/Supersonic 1-Spool Turbojet

• Subsonic 2-Spool Turbofan

• Subsonic 2-Spool Boosted Turbofan

• Subsonic 3-Spool Turbofan

• Analysis of the Thermodynamic Cycle

• Nozzle Area and Performance (Thrust, Power etc.) calculation

• Mass Flows (Core, Bypass, Fuel)

• Automatic calculation of ambient conditions based on the flight altitude using the International Standard Atmosphere model

• Automatic calculation of Cp, gama, R for each component based on temperature and Fuel to Air Ratio

• Automatic calculation of isentropic efficiency for each compressor and turbine based on polytropic efficiency and pressure ratio

Hybrid Precooled Rocket Engine at Design Point

• Analysis of the combined Thermodynamic Cycles with Air, Hydrogen & Helium as working fluids

Ramjet Engine at Design Point

• Simulation of the thermodynamic cycle of a hydrogen-fuelled Ramjet engine at optimized conditions.

Ramjet Engine at Design Point

• Simulation of the thermodynamic cycle of a hydrogen-fuelled Ramjet engine at optimized conditions.

Supersonic 2-spool Turbojet Engine at Design Point

• Simulation of the thermodynamic cycle of a Supersonic 2-spool turbojet engine with reheat.

Aircraft Emissions

• Emissions calculation for aircraft engines in LTO cycle and Cruise
• Type of turbofan engines used: 1. Subsonic 2-Spool, 2. Subsonic 3-Spool

Compressor Map Operating Point Prediction using

• Scaling Techniques on an existing HPC map
• Artificial Neural Networks to interpolate the existing map's data

Developer: Aggelos Gaitanis Original creator: Evangelia Pontika HyRE, Ramjet tab programmer: Spiros Tsentis Supersonic 2-spool Reheated tab programmer: Anastasios Saflekos Emissions tab developer/programmer: Maria Bakali Advisor: Ioanna Aslanidou, Konstantinos Kyprianidis Supervisor: Anestis Kalfas