Optimization of a Centrifugal Impeller Design Through CFD Analysis (July 1, 1993)

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N95- 23624 OPTIMIZATION OF A CENTRIFUGAL IMPELLER DESIGN THROUGH CFD ANALYSIS W.C. Chen, A. H. Eastland, D. C. Chan Rockwell International, Rocketdyne Division R. Garcia NASA, Marshall Space Flight Center / / / 31 This 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 resuits 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. 219

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Transcript of Optimization of a Centrifugal Impeller Design Through CFD Analysis (July 1, 1993)

Page 1: Optimization of a Centrifugal Impeller Design Through CFD Analysis (July 1, 1993)

N95- 23624

OPTIMIZATION OF A CENTRIFUGAL IMPELLER DESIGN

THROUGH CFD ANALYSIS

W.C. Chen, A. H. Eastland, D. C. Chan

Rockwell International, Rocketdyne DivisionR. Garcia

NASA, Marshall Space Flight Center

/

• / /

31

This 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 thesecond blade row offset circumferentially with respect to the first row. The

second approach is to control the high losses related to secondary flows withinthe 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 theeffect 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 dischargeleakage flow impacts and Rocketdyne will continue to work on the meridional

contour and the blade leading to trailing edge work distribution. This paper willalso present Rocketdyne resuits 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.

219

Page 2: Optimization of a Centrifugal Impeller Design Through CFD Analysis (July 1, 1993)

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