Abstract: An arrangement for the adjusting of rotor blades of a propfan turboprop engine equipped with two counter-rotating propfan rotors has a number of double-toothed planet wheels which are fastened in a rotatably disposed web. The web is supported on the side of the housing by planet members disposed on one of the propfan rotors. The two toothings of the planet wheels are in operative connection with ball spindle adjusting rings. Using an adjusting motor, a relative movement of the web can be achieved with respect to the housing, whereby the blades of two counter-rotating rotor blade rings can be swivelled. According to the invention, an adjustment of rotor blades will also be possible when no stationary housing parts are available for the support.

Abstract: In an arrangement for mounting a shrouded pivotable propfan blade at a rotor, the propfan blade is held in a dovetail mounting of a blade carrier and, by using a first securing device is fixed with respect to axial movements of the propfan blade. The blade carrier is secured with respect to radial movements by means of a second securing device, which is accessible from the outside. This permits a simple and fast mounting and demounting of the propfan blades.

Abstract: A gas turbine jet propulsion unit of multi-shaft-double-flow construction in which a front compressor or fan supplies compressed air into a secondary channel arranged coaxially to the propulsion unit axis and formed between outer and inner wall structures, from which a secondary air component is taken and blown out against the turbine housing structures for purposes of turbine component cooling; the secondary air channel extends essentially over the entire propulsion unit length or at least up to the area near the turbine housing structure while the secondary air component is taken off from the secondary flow by way of openings in the inner wall structure which are arranged in direct proximity of the respective turbine housing structure.

Abstract: An installation for the control of the fuel supply to the afterburner of a bypass jet propulsion unit which permits an individual modulation of the fuel flows to the different burner systems, namely, the ignition burner, the main burner in the inner flow and the burner in the bypass flow. For this purpose, separate fuel pumps are coordinated to the inner flow and the bypass flow. The two fuel systems of the inner flow are thereby so linked from a shifting and regulating point of view that they can be individually modulated without mutual reaction. The fuel system of the bypass flow is independent of the fuel system of the inner flow so that the modulation thereof also has no reaction on the fuel system of the inner flow.

Abstract: A cover arrangement is provided for covering radial rotors of turbo machines such as impellers of gas turbine engines. The arrangement includes two cover halves extending respectively one half of the circumferential distance around the impeller rotor and connected at the edge portions by connecting flanges. In order to accommodate a balancing of the cover arrangement and uniform spacing between the cover arrangement and the impeller, the cover halves are provided with rib portions which are evenly spaced around the perimeter and which are shaped and configured similarly to the connecting flanges. In preferred embodiments, the rib members and the connecting flanges are constructed with similar moments of inertia, thermal capacities, and bending resistances, to further assure uniformity around the periphery of the cover arrangement.

Abstract: A method of making a ceramic turbine wheel which includes making a ceramic ring, and providing a ceramic disc within the ring by supporting the external periphery of the ring and hot pressing a ceramic powder within the ring. Ceramic blades are then sintered to the external surface of the ring using a layer of metallic silicon between each blade and the ring. The ring and blades are produced by a reaction-sintering process.

Abstract: A cranking apparatus comprising a shaft within a sleeve for insertion into a machine casing containing a rotor. The shaft carries a friction wheel for tangentially engaging a circular surface on the rotor, so that when the shaft is rotated the rotor will be cranked. The shaft may be angularly adjusted with respect to the rotor axis, and the friction wheel resiliently urged against the rotor surface. The sleeve may carry a revolution counter engaging the shaft.