100% Hydrogen Aero Turbine Simulator

Micromix Combustor Cutaway & Velocity Vectors Nozzle Velocity: 82.4 m/s

64x Cryo-H2 Micro-Injectors Combustion: STABLE_LEAN

Delivered Thrust

68.5 kN

96% Throttle Spool

Turbine Inlet Temp

1,740 K

Blade Load: 91.5%

Flashback Margin

28.4%

SL: 2.40 m/s

Thermal NOx Index

4.12 g/kg

Zeldovich Reaction

CO2 Emissions

0.0 kg/h

Pure H2O Exhaust

Cryo LH2 Mass Flow

0.54 kg/s

3.82x Jet-A Vol

Thermodynamic Brayton Cycle (T-s Diagram)

Fuel Energy Density: LH2 vs Jet-A Baseline

Combustor Rig Controls

Power Lever Angle (PLA) 96%

Modulates core air mass flow and high-pressure compressor pressure ratio (OPR).

Equivalence Ratio (Φ) 0.58

Fuel/Air stoichiometry. Hydrogen permits ultra-lean burn down to Φ = 0.35 with rapid kinetics.

Micromix Swirl Intensity 42°

Vortex breakdown creates recirculation zones preventing H2 flame front flashback.

Water/Steam Dilution 8%

Injects closed-loop exhaust steam to quench peak adiabatic flame temp, slashing thermal NOx.

Combustion Physics Note: Hydrogen has a laminar flame speed (~2.5 m/s) 5x higher than kerosene (~0.4 m/s). Without high-velocity micromix injectors and high swirl dissipation, flame fronts propagate upstream into the fuel manifold (Flashback).