b N94-1 549 - NTRS - NASA

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for all Mach numbers. Eigenvalue. Stiffness. Problem. • Pressure rescaled so that all eigenvalues have tile same order of mag- nitude. Physical acoustic waves.

N94-1 549 (b

A COUPLED TURBULENT

IMPLICIT

SPRAY

SOLUTION

COMBUSTION

K.-H. The

METHOD

IN

FOR

PROPULSION

SYSTEMS

CHEN

University

of Toledo,

Ohio

and J.-S. Sverdrup

SHUEN

Technology,

Aerothermochemistry Internal NASA

Lewis

Fluid Research

Inc.,

Ohio

Branch

Mechanics

Division

Center,

Cleveland,

Ohio

OBJECTIVES

• Develop chemically low

Mach

• Calculate bine

an efficient reacting number turbulent

combustor.

and flows

robust at all

algorithm speeds,

for multi-phase with

emphasis

flow

in

on

flows. spray

combustion

a gas

tur-

MOTIVATION

Many

reacting

modern

flows

in propulsion

compressible rocket

motor

velocity gas

--

at closed

turbine

variation

wide end

cannot

algorithms,

range

--

of Mach

numbers, at nozzle

low subsonic

incompressible

be efficiently

from

velocity,

compressible to low-speed

desirable.

OUTLINES

EQUATIONS

Gas-Phase

-

Liquid-Phase

Equations Equations

• NUMERICAL

ALGORITHM

• NUMERICAL

TEST

RESULTS

• CONCLUSION • FUTURE

PLAN

FOR

near

zero

but

large

density

approach.

progress made in high-speed Extending application range

-

by

exit.

reacting flow codes based on TEACH-type lack of robustness for complex flows.

• GOVERNING

calculated

e.g.,

to supersonic

combustor precludes

Most low-speed inefficient and

Tremendous two decades.

flow CFD

devices

ALLSPD

CODE

technologies

flow CFD in past flow regime highly

-

GOVERNING

• Gas-Phase

Equations

o_

o_

o(_,- _.)

o(P- P_) = i_° + R,,

(1)

u

1/_ .//3 _/_

o p o

o o p

000 000 000

.... .... ....

h

h/fl-1

pu

pv

p

....

_/_ _/_ Y_/_ Y2/_

o o o o

o o o o

pg ?2

K y6 C

q=7

EQUATIONS

r

._

Y_

00 p

0

0 p

YN-I/fl

o

o



"

"

p

0 3

rI¢'-

tt),

if

Time

(ti)

u_I

L_ < r]_'-

u_l

where Lc - C3.14tz312/ e

t,=LU(2_/3) '/_. tt = --rln[1 • Spray

Time

step

- AT.p_

At.p.

=

a mln

-

LU(,Id'-

a_l)]

(t_, tl, Is, tg, ti)

(ts)

INTERACTION

1. Initialize 2.

Solve

3.

Evaluate

4.

Solve

gas

BETWEEN

and

liquid

liquid-phase

TWO

phase

PHASES

variables.

equations.

spray

source

gas-phase

term,

equations

Hr. and

update

gas-phase

variables. 5. Update

spray

No,

to step

Yes,

go go

source

to step

2.

TEST

Backward-Facing

• Evaporating

Turbulent

• Gas

Spray

Turbine

HI ?

4.

NUMERICAL

• Turbulent

term,

RESULTS

Step Spray

Combustion

Flow

Flow. Flow.

- non-reacting.

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