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Ceramics for the advanced automotive gas turbine engine: A look at a single shaft designThe results of a preliminary analysis of a single shaft regenerative design with a single stage radial turbine are presented to show the fuel economy that can be achieved at high turbine inlet temperatures, with this particular advanced design, if the turbine tip speed and regenerator inlet temperature are not limited. The engine size was 100 hp for application to a 3500 lb auto. The fuel economy was analyzed by coupling the engine to the auto through a continuously variable speed-ratio transmission and operating the system at constant turbine inlet temperature over the Composite Driving Cycle. The fuel was gasoline and the analysis was for a 85 F day. With a turbine inlet temperature of 2500 F the fuel economy was 26.2 mpg, an improvement of 18 percent over that of 22.3 mpg with a turbine inlet temperature of 1900 F. The turbine tip speed needed for best economy with the 2500 F engine was 2530 ft/sec. The regenerator temperature was approximately 2200 F at idle. Disk stresses were estimated for one single stage radial turbine and two two-stage radial-axial turbines and compared with maximum allowable stress curves estimated for a current ceramic material. Results show a need for higher Weibull Modulus, higher strength ceramics.
Document ID
19770016546
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Nosek, S. M. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1977
Subject Category
Mechanical Engineering
Report/Patent Number
E-9163
NASA-TM-X-73651
Meeting Information
Meeting: Army Materials Technol. Conf. Ceramics for High Performance Applications, 2
Location: Newport, RI
Country: United States
Start Date: March 21, 1977
End Date: March 25, 1977
Sponsors: DARPA, AMMRC, ERDA
Accession Number
77N23490
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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