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FIRST STEPS TOWARD SPACE - Smithsonian Institution Libraries

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NUMBER 10 111<br />

rocket combustion chambers have been developed<br />

elsewhere, but I should like to mention at this point<br />

my former colleague Meyer-Hartwig who devoted<br />

intensive studies to these topics.<br />

There are three significant effects which reduce<br />

the surface temperature: heat absorption by passing<br />

the cooling liquid through the porous wall, heat<br />

absorption by the evaporation of the cooling liquid,<br />

and the additional boundary layer consisting of the<br />

mass addition of cooling liquid at the surface of the<br />

wall. A temperature profile for the cooling of a solid<br />

and a porous wall is represented in Figure 14. At a<br />

gas temperature of 1100°C and a velocity of 600-<br />

700 m/s the surface temperature can be reduced to<br />

100°C applying 0.04 g/(s-cm 2 ) specific mass flow<br />

rate (Figure 15).<br />

Figure 16 shows the application of porous material<br />

in a rocket nozzle. At a chamber pressure of<br />

36 kp/cm 2 and a gas temperature of about 2500 °K,<br />

0.6 g/(scm 2 ) of cooling liquid were fed through the<br />

nozzle wall, which amounts to less than 2 percent of<br />

the main mass flow rate of the combustion chamber.<br />

The porous materials used for the research in sweatcooling<br />

were made from powdered steel and copper.<br />

The strength-to-weight ratio of this material was<br />

almost equal to that of the compact material.<br />

Boundary-layer<br />

Additional<br />

Boundary-layer<br />

Solid Wall Porous Wall<br />

.Cooling<br />

FIGURE 14.—Temperature profiles for solid and porous walls.<br />

WOO<br />

°c<br />

800<br />

600<br />

COO<br />

200<br />

\<br />

\<br />

\<br />

1 \<br />

I N s><br />

-" - —<br />

02 g/cm 2 sec 01<br />

k<br />

FIGURE 15.—Surface temperature as a function of specific<br />

coolant flow rate.<br />

Figure 17 shows different test bars, orifices, and<br />

rocket nozzles developed in our laboratories. The<br />

development of porous materials for sweat-cooling<br />

was started with nonmetallic ceramics, but in connection<br />

with steel constructions a lot of difficulties<br />

arose due to differing rates of thermal expansion.<br />

Pressure-gas<br />

Cooling -agent<br />

Jacket<br />

1 Cooling-distributer<br />

Two -part tiller<br />

FIGURE 16.—Sweat-cooled material nozzle.<br />

Sweating-nozzle

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