Abstract: A turbine blade has a platform and an airfoil extending from a root at the platform to a tip. The airfoil has an internal cooling passageway network including at least one trailing edge cavity. A group of trailing edge holes extends from the trailing edge to the trailing edge cavity and a group of tip holes extends from the tip to the trailing edge cavity.

Abstract: A suspension device for a ceiling fan includes a bracket mounted on the ceiling. A bearing seat is engaged in the bracket. A central hole is defined and extends through the bearing seat. A first slot and a second slot are defined in an inner periphery of the central hole. A first indention and a second indention are defined in a top portion of the bearing seat. A cover is mounted to the top portion of the bearing seat. The cover includes a first channel defined to communicate with the first slot and a second channel defined to communicate with the second slot and the second indention. A shaft is partially received in the central hole. A pin extends through the hollow shaft and has two opposite ends selectively engaged in the bearing seat.

Abstract: An attachment system for joining a blade to a hub is described. The system comprises a blade slot in the hub, a rail system positioned within the blade slot, a root portion of a blade positioned within the slot, and a bumper cooperating with the rail and contacting the blade root portion. The bumper has a central portion with first and second sides, a first pair of arms extending from the first side, and a second pair of arms extending from the second side. The central portion of the bumper includes a tab for positioning the bumper within a blade slot.

Abstract: A helicopter gimbal rotor arrangement includes a drive shaft with a rotor hub, a rotor blade holder arrangement, and a coupling membrane for transmitting the rotational drive moment from the rotor hub to the rotor blade holder arrangement. The coupling membrane includes a plate element made up of a plurality of concentric rings that are spaced apart radially by annular gaps and are connected to each other by respective connecting webs spanning across the gaps. This plate element as the coupling membrane provides torsional stiffness combined with bending flexibility to allow tilting motions of the rotor blade holder arrangement relative to the rotor hub. Plural plate elements connected in parallel provide a redundant fail-safe arrangement, while plural plate elements connected in series achieve increased flexibility for out-of-plane tilting.

Abstract: A compressor stator vane includes pressure and suction sides extending chordally between leading and trailing edges, and longitudinally between a root and a tip. The vane narrows in chord to a waist between the root and tip. The vane may also be bowed at its trailing edge in cooperation with the narrow waist.

Abstract: A process for operating multistage turbocompressors (2, 22, 42) with a plurality of controllers (15, 35, 55) which interact one with each other, in which each compressor stage has anti-surge control valves (5, 25, 45) of its own, which recycle into the suction lines (1, 21, 41) of their respective own compressor stage (2, 22, 42). The control is performed by flow computers (6,26,46) for calculating the suction flow and computers (7,27,47) for determining the minimum acceptable flow from the delivery head. A comparison unit (12, 32, 52) determines the difference between the set point (derived from delivery head) minus the actual value (flow) and whenever the actual value is too low compared with the set point, it brings about a gradual opening of the corresponding surge line control valves (5, 25 and 45) until the actual flow exactly corresponds to the flow set point, which depends on the particular delivery head.