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Optimization of a Centrifugal Impeller Design Through CFD AnalysisThis paper discusses the procedure, approach and Rocketdyne CFD results for the optimization of the NASA consortium impeller design. Two different approaches have been investigated. The first one is to use a tandem blade arrangement, the main impeller blade is split into two separate rows with the second blade row offset circumferentially with respect to the first row. The second approach is to control the high losses related to secondary flows within the impeller passage. Many key parameters have been identified and each consortium team member involved will optimize a specific parameter using 3-D CFD analysis. Rocketdyne has provided a series of CFD grids for the consortium team members. SECA will complete the tandem blade study, SRA will study the effect of the splitter blade solidity change, NASA LeRC will evaluate the effect of circumferential position of the splitter blade, VPI will work on the hub to shroud blade loading distribution, NASA Ames will examine the impeller discharge leakage flow impacts and Rocketdyne will continue to work on the meridional contour and the blade leading to trailing edge work distribution. This paper will also present Rocketdyne results from the tandem blade study and from the blade loading distribution study. It is the ultimate goal of this consortium team to integrate the available CFD analysis to design an advanced technology impeller that is suitable for use in the NASA Space Transportation Main Engine (STME) fuel turbopump.
Document ID
19950017204
Acquisition Source
Headquarters
Document Type
Conference Paper
Authors
Chen, W. C. (Rockwell International Corp. Canoga Park, CA., United States)
Eastland, A. H. (Rockwell International Corp. Canoga Park, CA., United States)
Chan, D. C. (Rockwell International Corp. Canoga Park, CA., United States)
Garcia, Roberto (NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1993
Publication Information
Publication: Eleventh Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion, Part 1
Subject Category
Fluid Mechanics And Heat Transfer
Accession Number
95N23624
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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