Experience with Integrally-Cast Compressor and Turbine Components for a Small, Low-Cost, Expendable-Type Turbojet Engine

A discussion regarding experiences with integrally-cast compressor and turbine components during fabrication and testing of four engine assemblies of a small (29 cm (11½ in.) maximum diameter) experimental turbojet engine design for an expendable application is presented. Various operations such as metal removal, welding, and re-shaping of these components were performed in preparation of fulls-cale engine tests. Engines with these components have been operated for a total of 157 hours at engine speeds as high as 38, 000 rpm and at turbine inlet temperatures as high as 1256 K (1800° F).