A solid rocket propellant grain having rocket propellant and a membrane in contact with the rocket propellant. The membrane includes a highly heat conductive pattern which affects the propellant burning rate through localized conductive heat transfer from the combustion zone and into the uncombusted propellant. Different geometries for the thermally conductive pattern produce different combustion results.

A fuel line of a turbo-machine having a conical screw connection, wherein the conical screw connection has at least one screw socket into which a sealing cone having a sealing cone surface and a sealing cone face of a screw connection body connected thereto is interlockingly inserted, and screw socket and screw connection body are directly or indirectly screwed to each other, wherein the sealing cone has a metallic, flat sealing element which is received in a receptacle of the sealing cone surface, wherein the flat sealing element is a metal which is softer than the material of the sealing cone.

An assembly is provided for rotational equipment. This assembly includes a metal seal carrier and a carbon seal element. The metal seal carrier includes a receptacle and a cylindrical carrier surface forming an outer peripheral boundary of the receptacle. The carbon seal element is seated in the receptacle. The carbon seal element includes a cylindrical element surface that is brazed to the cylindrical carrier surface.

A solid rocket propellant grain having rocket propellant and a membrane in contact with the rocket propellant. The membrane includes a highly heat conductive pattern which affects the propellant burning rate through localized conductive heat transfer from the combustion zone and into the uncombusted propellant. Different geometries for the thermally conductive pattern produce different combustion results.