Preliminary aerodynamic design methodology for aero engine lean direct injection combustors

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dc.contributor.authorSun, Xiaoxiao
dc.contributor.authorLiu, Yize
dc.contributor.authorSethi, Vishal
dc.contributor.authorLi, Jie
dc.date.accessioned2017-07-11T16:23:59Z
dc.date.available2017-07-11T16:23:59Z
dc.date.issued2017-06-21
dc.description.abstractThe Lean Direct Injection (LDI) combustor is one of the low-emissions combustors with great potential in aero-engine applications, especially those with high overall pressure ratio. A preliminary design tool providing basic combustor sizing information and qualitative assessment of performance and emission characteristics of the LDI combustor within a short period of time will be of great value to designers. In this research, the methodology of preliminary aerodynamic design for a second-generation LDI (LDI-2) combustor was explored. A computer code was developed based on this method covering the design of air distribution, combustor sizing, diffuser, dilution holes and swirlers. The NASA correlations for NOx emissions are also embedded in the program in order to estimate the NOx production of the designed LDI combustor. A case study was carried out through the design of an LDI-2 combustor named as CULDI2015 and the comparison with an existing rich-burn, quick-quench, lean-burn combustor operating at identical conditions. It is discovered that the LDI combustor could potentially achieve a reduction in liner length and NOx emissions by 18% and 67%, respectively. A sensitivity study on parameters such as equivalence ratio, dome and passage velocity and fuel staging is performed to investigate the effect of design uncertainties on both preliminary design results and NOx production. A summary on the variation of design parameters and their impact is presented. The developed tool is proved to be valuable to preliminarily evaluate the LDI combustor performance and NOx emission at the early design stage.en_UK
dc.identifier.citationJie Li, Xiaoxiao Sun, Yize Liu and Vishal Sethi, Preliminary aerodynamic design methodology for aero engine lean direct injection combustors, Aeronautical Journal, Vol. 121, Issue 1242, August 2017, pp. 1087-1108en_UK
dc.identifier.issn0001-9240
dc.identifier.urihttp//dx.doi.org/10.1017/aer.2017.47
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/12181
dc.language.isoenen_UK
dc.publisherCambridge University Pressen_UK
dc.rights©2017 Cambridge University Press. This is the Author Accepted Manuscript made available to view and download for personal research use only. Please refer to any applicable publisher terms of use.
dc.subjectLDIen_UK
dc.subjectpreliminary designen_UK
dc.subjectNOx emissionen_UK
dc.titlePreliminary aerodynamic design methodology for aero engine lean direct injection combustorsen_UK
dc.typeArticleen_UK

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