Abstract: A secondary air system for an aircraft engine comprises an air flow path communicating between a source of pressurized cooling air and an air consuming component. A filter is disposed in the air flow path upstream from the air consuming component. The filter has at least one of: openings of a size selected for capturing suspended particles; and a filter surface material for binding with chemical contaminants.

Abstract: An aircraft engine cooling air system is configured to provide cooling air to turbine components. The system has an airflow path extending from a source of cooling air to the turbine components. A baffle is disposed in the airflow path upstream of the turbine components. The baffle has a filtering surface defining a plurality of filtering holes sized to trap particulate matter suspended in the cooling air. A bypass passage is fluidly connected to the source of cooling air and the turbine components in parallel with the baffle so as to allow airflow to the turbine components when the filtering holes of the baffle are clogged.