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N95- 23626
CFD PARAMETRIC STUDY OF CONSORTIUM IMPELLER
Gary C. Cheng °, Y.S. Chen*, R. Garcia*, and R.W. Williams i
Abstract
Current design of high performance turbopumps for rocket engines requires effective and
robust analytical tools to provide design impact in a productive manner. The main goal of this
study is to develop a robust and effective computational fluid dynamics (CFD) pump model for
general turbopump design and analysis applications. A Finite Difference Navier-Stokes flow
solver, FDNS, which includes the extended k-e turbulence model and appropriate moving
interface boundary conditions, was developed to analyze turbulent flows in turbomachinery
devices. A second-order central difference scheme plus adaptive dissipation terms was employed
in the FDNS code, along with a predictor plus multi-corrector pressure-based solution procedure.
The multi-zone, multi-block capability allows the FDNS code to efficiently solve flow fields with
complicated geometry. The FDNS code has been benchmarked by analyzing the pump
consortium inducer, and it provided satisfactory results. In the present study, a CFD parametric
study of the pump consortium impeller was conducted using the FDNS code. The pump
consortium impeller, with partial blades, is a new design concept of the advanced rocket engines.
The parametric study was to analyze the baseline design of the consortium impeller and its
modification which utilizes TANDEM blades. In the present study, the TANDEM blade
configuration of the consortium impeller considers cut full blades for about one quarter chord
length from the leading edge and clocks the leading edge portion with an angle of 7.5 or 22.5
degrees. The purpose of the present study is to investigate the effect and trend of the TANDEM
blade modification and provide the result as a design guideline. A 3-D flow analysis, with a 103
x 23 x 30 mesh grid system and with the inlet flow conditions measured by Rocketdyne, was
performed for the baseline consortium impeller. The numerical result shows that the mass flow
rate splits through various blade passages are relatively uniform. Due to the complexity of blade
geometries, the TANDEM blade configurations were analyzed with the multi-zone grid structure.
Both the 7.5 °- and the 22.5°-clocking TANDEM blade cases utilized a 80K mesh system. The
numerical result of two TANDEM blade modifications indicates the efficiency and the head are
worse than those of the baseline case due to larger flow distortion. The gap between the
TANDEM blade and the full blade allows the flow passes through and heavily loads the pressure
side of the partial blade such that flow reversal occurs near the suction side of the splitter. The
flow split at the exit of impeller blades is very non-uniform for TANDEM blade cases, and this
will greatly induce the side load on the diffuser. Therefore, the TANDEM blade modification
in the present CFD analysis does not improve the performance of the consortium impeller.
r:y.-'_ e• •
SECA, Inc., 3313 Bob Wallace Ave., Suite 202, Huntsville, AL
Engineering Sciences, Inc., 4920 Corporate Dr., Suite K, Huntsville, AL
ED 32, NASA/Marshall Space Flight Center, Huntsville, AL
ED 32, NASA/Marshall Space Flight Center, Huntsville, AL
PRECEDING PAGE EILANK NOT FILMED
https://ntrs.nasa.gov/search.jsp?R=19950017206 2018-08-25T16:47:43+00:00Z
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