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NPSS Multidisciplinary Integration and AnalysisThe objective of this task was to enhance the capability of the Numerical Propulsion System Simulation (NPSS) by expanding its reach into the high-fidelity multidisciplinary analysis area. This task investigated numerical techniques to convert between cold static to hot running geometry of compressor blades. Numerical calculations of blade deformations were iteratively done with high fidelity flow simulations together with high fidelity structural analysis of the compressor blade. The flow simulations were performed with the Advanced Ducted Propfan Analysis (ADPAC) code, while structural analyses were performed with the ANSYS code. High fidelity analyses were used to evaluate the effects on performance of: variations in tip clearance, uncertainty in manufacturing tolerance, variable inlet guide vane scheduling, and the effects of rotational speed on the hot running geometry of the compressor blades.
Document ID
20060009942
Document Type
Contractor Report (CR)
Authors
Hall, Edward J. (Rolls Royce Corp. Indianapolis, IN, United States)
Rasche, Joseph (Rolls Royce Corp. Indianapolis, IN, United States)
Simons, Todd A. (Rolls Royce Corp. Indianapolis, IN, United States)
Hoyniak, Daniel (Rolls Royce Corp. Indianapolis, IN, United States)
Date Acquired
September 7, 2013
Publication Date
March 1, 2006
Subject Category
Aircraft Propulsion and Power
Report/Patent Number
E-15261
NASA/CR-2006-213890
Funding Number(s)
WBS: WBS 22-714-09-12
CONTRACT_GRANT: NAS3-98003
WBS: WBS 22-302-15-20
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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