Abstract: Fine particulate deposition testing was conducted with an effusion plate geometry representative of a gas turbine combustor liner. Preheated coolant air with airborne particulate was fed into an effusion plate test fixture ...

Abstract: The interaction of thermal barrier coating’s surface temperature with calcium magnesium aluminosilicate (CMAS) like deposits in gas turbine hot flowpath hardware is investigated. Small Hastelloy X coupons were coated in ...

Abstract: The structural and aerodynamic performance of a low aspect ratio SiC/SiC ceramic matrix composite (CMC) high pressure turbine (HPT) blade was determined. The application was a NASA notional single aisle aircraft engine to ...