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

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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

版本更新内容:A new engine model was developed called \"Supersonic 2-spool reheated engine\"