The present application provides a combustor for a gas turbine engine. The combustor may include a combustor can with a number of nozzles therein and a flow conditioner positioned around the combustor can. The flow conditioner may include a number of apertures therein.
FEDERAL RESEARCH STATEMENT
 This invention was made with government support under Contract No. DE-FC26-05NT42643, awarded by the U.S. Department of Energy ("DOE"). The United States has certain rights in this invention.