Experience with integrally-cast compressor and turbine components for a small, low-cost, expendable-type turbojet engineA discussion regarding experiences with integrally-cast compressor and turbine components during fabrication and testing of four engine assemblies of a small (29 cm (11-1/2 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 are performed in preparation of full-scale 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).
Document ID
19760039320
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Dengler, R. P. (NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 8, 2013
Publication Date
November 1, 1975
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
SAE PAPER 751048
Meeting Information
Meeting: National Aerospace Engineering and Manufacturing Meeting