National Aerospace Laboratory of Science Technology Agency

The Director of National Aerospace Laboratory of Science and Technology

Terashi Isago

Masayuki Niino

Ryuzo Watanabe

Akio Suzuki

Yoshimichi Masuda

Nobuyuki Yatsuyanagi

Masaki Sasaki

Junjiro Takekawa

Hiroshi Sakamoto

Hiromi Gomi

Etsuo Ohtsuki

Akinaga Kumakawa

Akiraga Kumakawa

In the cooling wall of a regenerative cooling rocket combustion chamber, the throat portion thereof in which the heat load is highest is formed of a porous material having a perspiring cooling action. The other portion in which the heat load is relatively low is designed to be cooled by conventional forced convection. By such a composite cooling system, a high cooling effect is provided and yet the pressure loss in the cooling passages is small and light weight and long life of the engine are attained concurrently.

Rocket combustion chamber cooling wall of composite cooling type and

The present invention is directed particularly to an improved method using owder metallurgy for the manufacture of the grooved cooling wall of a liquid-propellant rocket combustion chamber. The surface of an inner cylinder constituting the cooling wall is formed with cooling grooves, and these grooves are densely filled up with a filler such as paraffin wax. Thereafter, metal powder which will provide an outer cylinder is compression-molded to a predetermined thickness around the inner cylinder. This metal powder is the same material as the material of the inner cylinder. After the paraffin wax which is the filler is evaporated and removed, the compression-molded metal powder body is sintered in a furnace. During this sintering heat treatment, the inner and outer cylinders are rigidly joined together by the sintering reaction between the atoms of the inner cylinder and the atoms of the metal powder.

Method of manufacturing a rocket combustion chamber

Growing community of inventors

Shibata, Japan

Terashi Isago