Abstract: Disclosed is a variable guide vane arrangement for use in a high-load compressor having at least one axial-flow stage in turbomachines including gas turbine engines, comprising a plurality of guide vanes positioned radially adjacent one another about a circumference in the axial flow stage of the compressor, each vane having a low-pressure and a high-pressure side during operation; a plurality of generally disk shaped turntable members, each of the vanes being secured at its outer end to one of the turntable members and each of the turntable members being rotatably mounted about the circumference, the diameter of each of the turntable members being greater than the spacing between adjacent guide vanes; and each of the turntable members being generally round and having a cut-out portion on the side adjacent to the low-pressure side of the guide vane secured thereto.

Abstract: A fuel injection nozzle assembly for gas turbine drives has an injection nozzle mounted in a structural part forming an outer housing of the combustion chamber of the gas turbine and extends into a primary zone thereof. In order to prevent carbonizing of the nozzle, the nozzle has a cooling passage extending longitudinally therein and communicates with a passage supplying cooling air thereto. Advantageously, according to a preferred embodiment, the injection nozzle is formed by a central body having a fuel supply passage therein and an outer shielding member such that the cooling air passage is defined between the outer shielding member and the central body. Additionally, the central body is formed of material having the high thermal conductivity of copper while the outer shielding member is formed of a material having the high temperature resistivity and low thermal conductivity of nickel alloys.

Abstract: An annular reverse-flow combustion chamber for gas turbine engines which includes an annular chamber formed between an outer casing of the combustion chamber and a flame tube with the annular chamber being supplied with preheated air from a heat exchanger. The preheated air is directed to the flame tube for combustion, cooling or other purposes. The flame tube includes a flame tube head of a double-walled construction so as to define a further annular chamber which communicates with an air bleed line at a discharge end of a compressor so that air is taken directly from the compressor and supplied to the further annular chamber. A vaporizer pipe member is disposed at the flame tube head with at least one of the walls of the double-walled flame tube head being welded to the vaporizer pipe member.

Abstract: A gas turbine engine which includes an essentially axial-flow compressor drive turbine having at least one turbine stator and at least one turbine rotor and a reverse-flow annular combustion chamber arranged coaxially with a longitudinal centerline of the gas turbine engine. The turbine stator and turbine rotor are arranged in the gas turbine engine and sized for heat retentivity such that thermal expansion rates of the turbine stator and turbine rotor are substantially equal.

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 gas turbine engine which includes one of a radial compressor or a combined axial-radial compressor, a reversing annular combustion chamber, a compressor drive turbine and a gas generator rotor. The gas generator rotor is rotatably mounted in the gas turbine engine by way of at least one movable bearing and a fixed bearing. A bearing spider is provided for the fixed bearing and is disposed behind the radial compressor and in front of the compressor drive turbine. The bearing spider is designed with a box construction so as to resist axial forces.

Abstract: A dual labyrinth seal arrangement is provided for controlling the supply of sealing air to a bearing chamber of a gas turbine engine. The bearing chamber housing the bearing for a turbomachine shaft connecting a compressor stage with a gas generator turbine is surrounded by a second chamber. A first of the labyrinth seals is disposed between the shaft and the second chamber so as to reduce the pressure of a supply of high pressure sealing medium passing into the seal chamber. The second set of labyrinth seals are provided between the turbo shaft and the second chamber so as to reduce the pressure of sealing medium passing from the second chamber into the bearing chamber. In particularly preferred embodiments, a majority of the sealing medium is vented from the second chamber and supplied to the working cycle of the gas turbine engine, while the remaining smaller portion is supplied as sealing air into the bearing chamber via the second set of labyrinth seals.