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