The NASA high pressure facility and turbine test rigNASA Lewis Research Center is presently constructing a test facility for developing turbine-cooling and combustor technology for future-generation aircraft gas-turbine engines. Prototype engine hardware will be investigated in this facility at gas-stream conditions up to 2480 K average turbine inlet temperature and 4.14 million N/sq m turbine inlet pressure. The facility will have the unique features of fully automated control and data acquisition through the use of an integrated system of minicomputers and programmable controllers, which will result in more effective use of operating time and operators and will provide a built-in self-protection safety system. The facility, turbine rig, and turbine-cooling test program are described.
Document ID
19790037283
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Stepka, F. S. (NASA Lewis Research Center Turbine Cooling Section, Cleveland, Ohio, United States)