CFD parametric study of consortium impeller

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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