Jet engine turbine (3D xray blue transparent)

Predictive Simulation of nvPM Emissions in Aircraft Combustors

Project Number: 071
Category: Emissions, Aircraft Technology Innovation

Boundary layer ingestion (BLI) is a popular area of research by many entities in aerospace due to the potential for large fuel burn savings, but research on the noise implications of this technology is limited. The noise generated by the interaction of the engine fan and the aircraft boundary layer has relatively large uncertainties. The purpose of this project is to identify, develop, and validate a parametric module for a generic BLI engine that can predict the noise from the engine fan, taking into account the specifics of the aircraft and engine configuration and design. Parameters influencing the model include aerodynamic distortion parameters or others that may affect the noise of the propulsor. The module developed will be based on lower order methods but will seek to validate such methods against higher fidelity approaches and any publicly available experimental data sets.

Project 071 illustration
Schematic illustration of proposed multiscale/multistage approach towards a predictive simulation of soot emission in jet engine combustors.

Outcomes

This project will advance the state-of-art in modeling soot formation and emission processes for aircraft engine combustors to enable innovative means to reduce these emissions. Use of real jet fuel chemistry will highlight the impact of fuel components and their reaction pathways on soot formation, and hence would be of direct relevance to legacy and next generation aircraft engines. Integrating these sub-models in LES will enable study of realistic gas turbine configurations. The proposed work addresses knowledge gaps, leveraging and building upon a long history of fundamental and modeling strategies at Georgia Institute of Technology, University of Michigan, and United Technology Research Center (UTRC).

Last updated 7/7/2020