Abstract: A heat exchanger having an inlet duct for admission of a first fluid to be heated, an outlet duct for discharge of the first fluid after heating thereof, the ducts being arranged in substantially parallel relation, and an assembly of a plurality of heat exchanger tubes connected to the inlet and outlet ducts for receiving the first fluid from the inlet duct to convey the first fluid through the tubes for discharge into the outlet duct. The heat exchanger tubes are of U-shape each including a curved bend region in which reversal of direction of flow of the first fluid is effected. The assembly of heat exchanger tubes extends laterally of the ducts into the path of travel of a second fluid which flows around the tubes in a passage area to effect heat exchange with the first fluid in the tubes.

Abstract: A heat exchanger having an inlet duct for admission of a first fluid to be heated, an outlet duct for discharge of the first fluid after heating thereof, the ducts being arranged in substantially parallel relation, and an assembly of a plurality of heat exchanger tubes connected to the inlet and outlet ducts for receiving the first fluid from the inlet duct to convey the first fluid through the tubes for discharge into the outlet duct. The heat exchanger tubes are of U-shape, each including first and second straight leg portions respectively connected to the inlet and outlet ducts and a curved bend region connecting the straight leg portions for reversing the direction of flow of the first fluid from the first leg portion to the second leg portion. The assembly of heat exchanger tubes projects laterally of the ducts into the path of travel of a second fluid which flows around the tubes in a passage area.

Abstract: A self-acting gap seal for a gap existing between individual modules of a composite, annular pressure vessel comprising a flat, thin-walled seal element on the inside of the pressure vessel to bridge the gap plus the circumferential region adjacent the gap. Internal pressure urges the seal element against the inner wall of the vessel to close and seal the gap to prevent exit of the pressure medium in the vessel.

Abstract: A heat exchanger collector comprising a plurality of connecting tubes, where sets of connecting tubes arranged side by side in a plane are superimposed in layers one on the other for an interlocked connection with mating profile elements inserted in the tube end area. In order to produce a closed wall of the collector, the connecting areas between the tube ends and the mated elements are joined together by, e.g., brazing to prevent the ingress of fluids. The sealed joint to exclude liquids can be achieved also successively in the layer-by-layer construction. The profile elements have recesses for the tubes and further blind recesses for flexibility and thermal effects.

Abstract: A turbine blade, more particularly a turbine nozzle vane, for a gas turbine engine, consisting of a structural metallic core enveloped at a distance by a ceramic blade jacket. Through provision a primarily highly heat-resistant, ceramic metal compound structure of the blade, the blade jacket is compressively prestressed spanwise between the blade shrouds in the inoperative condition of the turbine and where said compressive prestressing of the blade jacket, produced during assembly and which exists in the inoperative condition, is at least maintained during the operation condition by selecting for the metallic core of the blade, a material of average coefficient of thermal expansion and for the metallic inner and outer shrouds of the blade, and for the inner and outer metallic, sleeve-like components producing the axial prestress, materials of higher coefficients of thermal expansion, and for the highly thermally stressed ceramic blade jacket, a material of average coefficient of thermal expansion.

Abstract: A gas turbine having a rotor including a ceramic turbine wheel and a rotor shaft formed in part of ceramic material, the wheel and ceramic shaft portion being formed as one piece. The ceramic shaft portion extends into a cooler zone of the engine where it is connected to a steel shaft portion. The ceramic shaft portion is supported by a radial bearing, preferably an air bearing. A ceramic disk projects radially from, and is formed as one piece with, the ceramic shaft portion, the disk cooperating with a thrust bearing, preferably an air bearing.

Abstract: A turbine wheel including blades and rim made in one piece, a notch in the peripheral surface of the rim between each two successive blades, and a through-hole in the rim radially inwardly of and parallel to each notch. The through-holes permit cooling air to flow from one side of the turbine wheel to the other. Each through hole is spaced closely to its respective notch to define a narrow rated breaking point between the two. The through-holes may be of circular, oval, or elliptical cross-sectional shape. A tubular baffle is arranged in each through-hole, the baffle being open at one end to receive cooling air, but the other end of the baffle being blocked. The wall of the baffle is perforated. Longitudinally-extending webs may support each baffle in spaced relation to the wall of the through hole. Annular plates may be arranged over opposite sides of the wheel to define air flow openings to and exhaust openings from the through-holes.