New England Research & Development, LLC — Department of Defense SBIR Phase I: N171-034

Description

There are numerous conditions where gas turbine engines ingest small particulates. Of particular concern are the particles (~1-10 micrometer) that are ejected into the atmosphere as volcanic ash. Ingestion of these particles has numerous detrimental effects. Particle collisions cause abrasion of compressor blades, leading to loss of efficiency. Ingested particles that partially or completely melt in the combustion region can deposit on downstream structures, leading to decreased airflow. These particles usually cannot be removed and may require replacement of the engine. Such particles also plug the small holes used for film cooling of turbine blades and nozzle guide vanes, leading to blade overheat and failure. The proposed research will develop a discrete-element method for the transport, reaction, collision and adhesion of small particles in a gas turbine engine. This model will be developed to be incorporated with existing CFD codes. This tool will allow engine designers to assess the vulnerability of their designs to ingested particles and to examine the efficacy of proposed mitigation strategies. Since both military and commercial aircraft are subject to performance degradation due to ingested particles we anticipate interest from military, commercial and industrial gas turbine designers and manufacturers.