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Two-Stage Axial Compressor Rig Designed To Develop and Validate Advanced Aerodynamic TechnologiesFuture aeropropulsion gas turbine engines must be affordable in addition to being energy efficient and environmentally benign. Progress in aerodynamic design capability is required not only to maximize the specific thrust of next-generation engines without sacrificing fuel consumption, but also to reduce parts count by increasing the aerodynamic loading of the compression system. To meet future compressor requirements, the NASA Glenn Research Center is investigating advanced aerodynamic design concepts that will lead to more compact, higher efficiency, and wider operability configurations than are currently in operation.
Document ID
20050214834
Acquisition Source
Glenn Research Center
Document Type
Other
Authors
Larosiliere, Louis M. (Army Research Lab. Cleveland, OH, United States)
Date Acquired
September 7, 2013
Publication Date
March 1, 2003
Publication Information
Publication: Research and Technology 2002
Subject Category
Aircraft Propulsion And Power
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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