The design of a modern aero-engine combustor is strongly driven by severe emission regulations. The paper describes an automated preliminary aero-thermal design process for a rich-burn combustor by combining different low fidelity analysis tools in order to speed up the preliminary design loop and provide improved combustor designs. Design evaluation is performed by a knowledge-based preliminary design tool coupled with a network solver. The preliminary design tool provides a 2D geometry model and cooling layout based on industrial in-house design rules. The 1D network solver then calculates the air distribution inside the combustor for two state-of-the-art combustor cooling schemes, i.e., single skin cooling and double skin tiled cooling. The computed air distribution is subsequently used to predict emissions which are minimized by using a genetic multi-objective optimization algorithm. As a result, better designs are obtained with the prescribed approach compared to a human reference design.
Nomenclature, c i,j = flow/geometry specific constants λ = node mass source afr 1 = air-fuel-ratio of injector ρ = fluid density afr 2 = air-fuel-ratio at primary zone exit Indices c = port style • cc = combustor chamber cb = circumferential blockage factor • i,o = inner/inlet, outer/outlet f r = radial factor • m = middle d = diameter • p = port h, h = height, constraint vector • pp,sp = primary/secondary ports l = length • pz,sz = primary/secondary zones = mass flow • 3 = compressor exit n = number • 4 = turbine entry p = pressure • TO = take-off conditions p = parameter vector Abbreviations r = radius CFD = computationalsfluid dynamics s i,j = flow direction at node i,j NO x = nitrogen oxides v = velocity NSGA-II = non-dominated sorting V = volume genetic algorithm-II α = combustor cant angle SN = smoke number