Pratt & Whitney Rocketdyne, Inc.

The Boeing Company

Rockwell International Corporation

Sherwin Yang

Nathan J Hoffman

Michael P Moriarty

Gregory A Johnson

Adon Delgado, Jr

Alan V Von Arx

Daniel Edward Matejczyk

William Determan

Kathleen M Sevener

Gerard D Pelletier

Kuang-Tsan K Chiang

A method of forming a nanocomposite thermoelectric material having microstructural stability at temperatures greater than 1,000&#xb0; C. The method includes creating nanocrystalline powder by cryomilling. The method is particularly useful in forming SiGe alloy powder.

High temperature stable nanocrystalline SiGe thermoelectric material

A heat transfer tube includes a container, a cavity within the container, and a heat transfer medium located within the cavity. The heat transfer medium consists essentially of a solid-gas suspension of a gas and a substantially homogeneous nanoparticle powder located within the cavity. The cavity is in a partial vacuum state. The nanoparticle powder comprises Ca(OH), LiH, ZrH, or Mg(OH)in a solid state and is capable of substantially freely emitted and reabsorbing the gas as a function of temperature.

Nano-particle wave heat pipe

Methods and apparatus are provided for a shield to protect a surface from the impact of hyper-velocity projectiles. The apparatus comprises a foam material that is configured to cover the surface to be protected and is attached directly to that surface. A coating material is typically disposed on the outer surface of the foam material and may penetrate the foam material to a predetermined depth. The foam material and the coating material are selected to form a composite having predetermined values of sonic velocity, toughness, and thermal conductivity. The composite of foam material and coating material can be significantly lighter in weight than a metal shield having equivalent protective characteristics.

Lightweight protector against micrometeoroids and orbital debris (MMOD) impact using foam substances

Copper alloy rocket engine combustion chamber linings have been found to deteriorate when exposed to cyclic reducing/oxidizing (redox) environments which are a consequence of the combustion process. This deterioration, known as blanching, can be characterized by increased roughness and bum through sites in the wall of the combustion chamber lining and can seriously reduce the operational lifetime of the combustion chamber. The blanching problem can be significantly reduced by depositing a thin layer of Cu-30.sup.v /.sub.o Cr (a copper matrix with 30.+-.10 volume percent of chromium) on the inside wall of the combustion chamber. The microstructure of the Cu-30.sup.v /.sub.o Cr coating consists of finely distributed chromium (Cr) particles in a copper (Cu) matrix. When exposed to an oxidizing environment at high temperatures, the coating forms a protective chromium scale which is stable in hydrogen atmospheres (e.g., substantially unreduced by high pressure hydrogen). The Cu-30.sup.v /.sub.o Cr coating can be applied, for example, using low temperature arc vapor deposition or low pressure plasma spray techniques.

Blanching resistant coating for copper alloy rocket engine main chamber

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Chatsworth, CA, United States of America

Sherwin Yang