This thesis pertains to development of preliminary combustor design tools for prediction of NOx emissions from aircraft gas turbine combustors. These tools are developed in the form of chemical reactor models and their objective is to predict the formation of NOx based on combustor geometry and engine input parameters such as inlet pressure, inlet temperature, fuel flow and air flow. The construction of the reactor networks follow from cold flow computational fluid dynamics results as it provides a way for allocating volumes to each reactor in the network. The ability of the model to predict NOx has been analysed by comparing predictions with measured data and theoretical trends. The model predictions for different combustors satisfy theoretical trends across various thrust levels in that the model correctly captures the effect of various input parameters on NOx formation and predicts most power conditions for various combustors within 15% of the measured value.
| Identifer | oai:union.ndltd.org:LACETR/oai:collectionscanada.gc.ca:OTU.1807/43987 |
| Date | 17 March 2014 |
| Creators | Lanewala, Hasnain |
| Contributors | Sampath, Sam, Groth, Clinton P.T. |
| Source Sets | Library and Archives Canada ETDs Repository / Centre d'archives des thèses électroniques de Bibliothèque et Archives Canada |
| Language | en_ca |
| Detected Language | English |
| Type | Thesis, Image |
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