Longitudinal Mode Aeroengine Combuston Instability: Model and Experiment

Combustion instabilities in gas turbine engines are most frequently encountered during the late phases of engine development, at which point they are difficult and expensive to fix. The ability replicate an engine-traceable combustion instability in a laboratory-scale experiment offers the opportunity to economically diagnose the problem more completely (to determine the root cause), and to investigate solutions to the problem, such as active control. The development and validation of active combustion instability control requires that the causal dynamic processes be reproduced in experimental test facilities which can be used as a test bed for control system evalitation. This paper discusses the process through which a laboratory -scale experiment can be designed to replicate an instability observed in a developmental engine. The scaling process used physically- based analyses to preserve the relevant geometric, acoustic and thermo-fluid features, ensuring that results achieved in the single-nozzle experiment will be scaleable to the engine. Pres: Symposium RTO Applied Vehicle Tech Panel (AVT), Braunschweig, Germany,p5-1/5-10, 8-11 May 2000. This article is from ADA395700 Active Control Technology for Enhanced Performance Operational Capabilities of Military Aircraft, Land Vehicles and Sea Vehicles (Technologies des systemes a commandes actives pour l'amelioration des performances operationnelles des aeronefs militaires, des vehicules terrestres et des vehicules maritimes)