Future 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.
Two-Stage Axial Compressor Rig Designed To Develop and Validate Advanced Aerodynamic Technologies
2003-03-01
Miscellaneous
No indication
English
Aerodynamic design of a highly loaded supersonic aspirated axial flow compressor stage
Online Contents | 2014
|Aerodynamic Optimization of a Single-Stage Axial Compressor with Stator Shroud Air Injection
Online Contents | 2017
|AIAA-2005-1137 AERODYNAMIC ROTATING VORTEX INSTABILITY IN A MULTI-STAGE AXIAL COMPRESSOR
British Library Conference Proceedings | 2005
|Aerodynamic Optimization of a Single-Stage Axial Compressor with Stator Shroud Air Injection
Online Contents | 2017
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