Swirled Lean Fully Premixed Flame Scaling from Laboratory Experiment to Turbofan

This article describes a framework to scale hydrogen fully premixed swirled flames between laboratory experiment and turbofan’s combustor. The framework combines three major elements: 1) turbomachinery calculations, 2) combustor performance maps, and 3) flame stabilization and matching conditions for scaling. First, the operating point of the engine is determined with a thermodynamics-based analysis applied to all components of the engine: fan, compressor, combustor, and turbine. Second, the method to obtain and compute the combustor’s operating point in the fully premixed mode, coined the combustor performance map, is applied. The method includes six requirements: the thermal power for the engine, mass, momentum, energy conservation budgets in the combustor, a revisited compressor/combustor/turbine power balance for fully premixed combustion, and a coupling relationship. The results are synthesized as combustor performance maps that are functions of flame equivalence ratio [Formula: see text] and injector flow split [Formula: see text]. The flame stagnation temperature, [Formula: see text] species mass fraction, and emission index are reported on these maps. The flow split and flame equivalence ratio of the operating point are deduced from these requirements. Third, a theoretical method to scale lean fully premixed swirled flames between the laboratory experiment and the jet engine at the determined conditions is described based on the criterion for stabilization.