COMBUSTION RESEARCH & FLOW TECHNOLOGY INC — Department of Defense STTR Phase I: N17A-T003

Description

The primary objective of this effort is to develop a tractable computational tool to assess the probability of ignition within aircraft combustors and augmentors during routine igniter and/or system design analysis. This computational tool will provide for the off-line assessment of ignition probability given flowfield simulation data, characteristic igniter geometric and physical parameters, and igniter location(s) within the flow. This formulation will employ detailed physical modeling of all phases of the ignition kernel development within a Lagrangian formulation to determine the probability that a fully developed turbulent flame may be established within the combustor or augmentor. Additionally, a reduced order run-time LES ignition model will be developed based on a reduction of the detailed off-line model. This run-time model will be implemented as an application programming interface (API) or user defined function (UDF) within commercial flow solvers commonly used by combustor and augmentor OEMs. This proposed off-line modeling approach will provide the NAVY and NAVY OEMs with the ability to routinely assess combustor and augmentor ignition schemes and designs within parametric trade studies. The run-time modeling approach will also provide the NAVY with the capability to assess ignition induced transient events within combustors and augmentors prior to steady state operation.