Aircraft Engine Technology (AET)

Aircraft Engine Technology — Humanitarian STOL Turbofan. Team design of a two-spool high-bypass turbofan for a relief-mission transport requiring short take-off/landing and low cruise fuel burn. The engine was sized and optimised with GasTurb, then detailed via preliminary compressor/turbine design, stress checks, and CAD.

Result: 88% (highest mark out of 15 teams).

We chose a STOL-capable humanitarian aircraft and set cruise as the design point to minimise TSFC subject to off-design thrust/temperature limits. A parametric study (BPR, fan/booster split, HPC PR, mass flow, Tt4) defined a feasible space under OPR and static-thrust constraints. The final layout uses a fan+booster (LPC), multi-stage HPC, and two-stage HPT/LPT sized for cruise with margins at take-off and climb.

Full engine CAD render
Full-engine CAD render
Blade set CAD
3D blade geometries: (a) LPC rotor, (b) HPC rotor, (c) HPT rotor, (d) LPT rotor
Geometry — assembly and blade set
Engine schematic — dimensions
2D drawing — principal dimensions (Blue — Fan, Green — High Pressure Spool, Red — Low Pressure Spool)
Engine schematic — components
Engine schematic — components (A–L)

Component key

Label Component
A Fan
B Inlet guide vanes
C Low-pressure compressor
D Strut
E High-pressure compressor
F High-pressure spool
G Combustor
H High-pressure turbine
I Low-pressure spool
J Low-pressure turbine
K Rotor
L Stator
GasTurb parameter optimisation
GasTurb parameter optimisation
HPC PR vs BPR trade study
HPC PR vs bypass ratio trade
Parametric studies — operating-point selection
Turbine design flow chart
Turbine preliminary design flow