Recursive sequential combustion using a discrete sector approach

Authors

Fabrice Louis Michel Giuliani - Combustion Bay One e.U., Austria
Andrea Hofer - Combustion Bay One e.U., Austria

Abstract

Recursive sequential combustion is a novel concept developed by CBOne that maximises the interaction of circulated burnt gases with the reactants in the combustor of a gas turbine to improve combustion performance. The idea is basically to place all the burners right behind each other in the closed-loop corresponding to the annular combustor and have the inlets coming and the burnt gases getting out from the side walls. Technically, the challenge is to design the flow properly so that this principle can run effectively on the whole operation range without failure. First, this article reviews the advantages of this technology versus conventional. The flow dynamics are entertained by the elevated momentum flux at the inlets. The effect of the heat conservativeness of the hot core on the lean combustion robustness is rated regarding the lean blowout limits. The hote core heat conservativeness connects to the permanent circulation of constantly renewed burnt gases. Another benefit is the recursive reburning effect that improves the NOx performance. Second, a combustor design is presented and detailed. The CFD study and the experiments done using this design are discussed. Third, the adequacy of additive manufacturing, and the vision of an all integrated combustor that sums up all functions between the last compressor stage and the first turbine stage are discussed. This approach can save substantially weight and congestion, which is of interest for airborne applications.