Abstract: The hollow shaft of a high pressure compressor is provided in a conically tapering section downstream of the last rotor disc on its inner surface with a vane-like rib arrangement for conveying a stream of cooling air from the vicinity of the axis of the shaft into the outer peripheral regions of the last rotor disc. The stream then passes through corresponding circumferentially distributed axial holes in the rotor disc. In this way, better cooling of the last compressor stages which have been heated by the main stream of air in the compressor and a reduction in the stresses in the structural parts can be obtained.

Abstract: The conical section of the hollow shaft of a high pressure compressor behind the last rotor disc is surrounded by an annular protective shield. The shield serves to protect the hollow shaft and the last rotor disc from the main stream of hot compressed air leaving the compressor. Between the hollow shaft and the heat shield a stream of cooling air is furthermore conducted from the vicinity of the axis to the outer region of the last rotor disc. The stream of air then passes through corresponding circumferentially distributed axial holes in the last rotor disc.

Abstract: This invention covers elements, such as guide walls, shut-off flaps, flow dividers and vanes, arranged on or in flow ducts energized with compressor and/or fan air, where said elements are variably arranged to suit variable operating states. To achieve extremely accurate, light-weight and uncomplicated actuating kinematics, the elements are designed as memory-alloy components or are nonpositively connected to at least one such component, they are at least partially located at one end and they permit of selective deformation in response to operationally induced over-maximum or under-minimum temperature conditions.

Abstract: This device provides the diffusor guide vanes with bypass ducts which establish communication between the pressure and suction sides, which can be sealed by means of shut-off elements, which take the form of bimetal components or at least are connected to such a component, and which are deformed flap-fashion as a function of temperature.

Abstract: An apparatus for optimizing blade and sealing slots of a compressor of a gas turbine comprising a rotor including a plurality of axially spaced discs and rotor blades on the discs and a stator casing surrounding the blades and forming clearance slots therewith. The blades and stator casing form a path for flow of air in a main stream in which the air is compressed and discharged at a discharge end of the compressor. A seal at the last of the discs opposes outflow of compressed air thereat and forms sealing slots through which leakage air can flow from the main stream. The leakage air is conveyed from the compressor and a portion thereof is diverted as a secondary stream in a direction opposite the main stream of air flow in the compressor, and discharged towards the last rotor disc and at least the next adjacent rotor disc to flow thereon.

Abstract: A rotor of a flow machine has a circumferentially extending slot with laterally projecting flanks. A plurality of rotor blades have roots radially locked in the circumferential slot. The rotor blades have pedestals substantially level with the surface of the rotor, and the blade roots or feet are circumferentially slidable in the circumferential slot. The circumferential slot has a blade stacking hole for inserting the blade roots into the slot. A locking device is positioned between the roots of a pair of blade elements. The locking device has a lock foot shaped to engage the sides of the adjacent blade roots. The sleeve is radially movable with the lock foot and rotatable about its own axis. The lock foot is not rotatable. The sleeve has a pair of outwardly extending tangs. A coil spring extends between the bottom of the circumferential slot and the sleeve to urge the sleeve and the lock foot radially outwardly.