Abstract: A rotary ring seal with gas-dynamic lubrication for high-speed turbomachines, particularly gas turbine engines, in which one of two complementary rings is radially perforated with apertures which extend in parallel with the ring sealing face and which are supplied with a cooling liquid. In order to achieve a durable seal, particularly with regard to high temperatures and speeds, a circumferentially periodically uniformly increasing and decreasing number of holes extending through the mating ring provide for the generation of a periodically alternating temperature and, consequently, an axial-expansion zone of the ring so as to produce a periodically uniformly undulated sliding surface on the mating ring which corresponds to the lubricant wedge profile of a gas-dynamic thrust bearing.

Abstract: A composite gas turbine engine including a fan, a lift device, a compressor, and a turbine for operating the fan, lift device, and compressor. An inner annular duct leads air from the fan to the compressor and turbine, and an outer annular duct leads air from the fan so that it bypasses the compressor and turbine. A supercharger is located between the fan and compressor and within the inner duct. A drive shaft rotated by the turbine is alternatively coupled either to the fan or to the supercharger and lift device. The supercharger raises air pressure flowing to the compressor to a greater degree than does the fan. The drive shaft is connected to a fan shaft and a supercharger shaft through a gearset, and brakes are provided for arresting the motion of the latter two shafts. A third duct leads from the fan to the inner duct while bypassing the supercharger, and means are provided for optionally guiding air into the third duct when the fan is operating, or to the supercharger when the fan is immobilized.